From 1a27fc0227f1c935723f95cff49d5a90eef4c66c Mon Sep 17 00:00:00 2001 From: Peter Sharpe Date: Mon, 19 Feb 2024 12:30:16 -0500 Subject: [PATCH] Add new airfoils from tracfoil database to airfoil database --- .../airfoil/airfoil_database/AV-1.7-8.dat | 114 ++++ .../airfoil/airfoil_database/BE5030FVNC2t.dat | 143 +++++ .../airfoil/airfoil_database/BE5045FVNC2t.dat | 103 ++++ .../airfoil/airfoil_database/BE5655FVNC2t.dat | 123 +++++ .../airfoil_database/DP1,68-8,37_DS.dat | 262 +++++++++ .../airfoil_database/DP1,72-8,16_DS.dat | 262 +++++++++ .../airfoil_database/DP1,72-8,32_DS.dat | 261 +++++++++ .../airfoil_database/DP1,77-8,23_DS.dat | 262 +++++++++ .../airfoil_database/DP1,79-8,37_DS.dat | 262 +++++++++ .../airfoil_database/DP1,82-8,21_DS.dat | 262 +++++++++ .../airfoil_database/DP1,87-9,07_DS.dat | 262 +++++++++ .../airfoil_database/DP2,00-8,55_DS.dat | 262 +++++++++ .../airfoil_database/DP2,05-8,65_DS.dat | 262 +++++++++ .../airfoil_database/DP2,06-8,67_DS.dat | 262 +++++++++ .../airfoil_database/DP2,47-9,48_DS.dat | 262 +++++++++ .../airfoil/airfoil_database/Edge_Root.dat | 260 +++++++++ .../airfoil/airfoil_database/Edge_Tip.dat | 258 +++++++++ .../airfoil/airfoil_database/HL73-650rev.dat | 105 ++++ .../airfoil/airfoil_database/HL74-550rev.dat | 44 ++ .../airfoil/airfoil_database/HL75-K-3rev.dat | 49 ++ .../airfoil/airfoil_database/MS3-11Retro.dat | 141 +++++ .../airfoil/airfoil_database/MS3-13Retro.dat | 141 +++++ .../airfoil/airfoil_database/MS3-14Retro.dat | 142 +++++ .../airfoil/airfoil_database/MS3-15Retro.dat | 141 +++++ .../airfoil/airfoil_database/PW106.dat | 164 ++++++ .../airfoil/airfoil_database/PW1211.dat | 265 ++++++++++ .../airfoil/airfoil_database/PW51i.dat | 164 ++++++ .../airfoil/airfoil_database/PW75.dat | 164 ++++++ .../airfoil_database/RZ10.00-225-235.dat | 102 ++++ .../airfoil/airfoil_database/S5020-2087.dat | 61 +++ .../airfoil/airfoil_database/Zone-21.dat | 259 +++++++++ .../airfoil/airfoil_database/Zone-25.dat | 260 +++++++++ .../airfoil/airfoil_database/Zone-36.dat | 260 +++++++++ .../airfoil/airfoil_database/Zone-40.dat | 260 +++++++++ .../airfoil/airfoil_database/Zone-46.dat | 260 +++++++++ .../airfoil/airfoil_database/Zone-52.dat | 260 +++++++++ .../airfoil/airfoil_database/ami43.dat | 124 +++++ .../airfoil/airfoil_database/avx-nitro.dat | 263 +++++++++ .../geometry/airfoil/airfoil_database/avx.dat | 66 +++ .../airfoil/airfoil_database/az2007_emp.dat | 143 +++++ .../airfoil/airfoil_database/az2007_ext.dat | 143 +++++ .../airfoil/airfoil_database/az2007_moy.dat | 143 +++++ .../airfoil/airfoil_database/az_2003_emp.dat | 144 +++++ .../airfoil/airfoil_database/az_2003_ext.dat | 144 +++++ .../airfoil/airfoil_database/az_2003_moy.dat | 144 +++++ .../airfoil_database/az_2004_9_1.4.dat | 144 +++++ .../airfoil/airfoil_database/az_2005_emp.dat | 144 +++++ .../airfoil/airfoil_database/az_2005_ext.dat | 144 +++++ .../airfoil/airfoil_database/az_2005_moy.dat | 144 +++++ .../airfoil/airfoil_database/azavempT.dat | 147 ++++++ .../airfoil/airfoil_database/azavextT.dat | 66 +++ .../airfoil/airfoil_database/azavmoyT.dat | 147 ++++++ .../airfoil/airfoil_database/azcombat1.dat | 64 +++ .../airfoil/airfoil_database/bc30.dat | 154 ++++++ .../airfoil/airfoil_database/bc50.dat | 154 ++++++ .../airfoil/airfoil_database/bc70.dat | 175 ++++++ .../airfoil/airfoil_database/be6568.dat | 147 ++++++ .../airfoil/airfoil_database/be6699.dat | 146 +++++ .../airfoil/airfoil_database/cb2012.dat | 45 ++ .../airfoil/airfoil_database/cb2195-25d.dat | 258 +++++++++ .../airfoil/airfoil_database/cb2195.dat | 55 ++ .../airfoil/airfoil_database/cb2513.dat | 45 ++ .../airfoil/airfoil_database/cb2514.dat | 45 ++ .../airfoil/airfoil_database/cb2515.dat | 45 ++ .../airfoil/airfoil_database/cb3013.dat | 45 ++ .../airfoil/airfoil_database/cb3512.dat | 45 ++ .../airfoil/airfoil_database/cristal.dat | 47 ++ .../airfoil/airfoil_database/dp189-7831.dat | 93 ++++ .../airfoil/airfoil_database/ds19.dat | 148 ++++++ .../airfoil/airfoil_database/ds21.dat | 265 ++++++++++ .../airfoil_database/du06-w-200-selig.dat | 204 +++++++ .../airfoil/airfoil_database/e193gu.dat | 98 ++++ .../airfoil/airfoil_database/eiffel33.dat | 403 ++++++++++++++ .../airfoil/airfoil_database/eiffel36.dat | 403 ++++++++++++++ .../airfoil/airfoil_database/eiffel371.dat | 405 ++++++++++++++ .../airfoil/airfoil_database/emx07.dat | 62 +++ .../airfoil/airfoil_database/fad05.dat | 104 ++++ .../airfoil/airfoil_database/fad05_CNC.dat | 80 +++ .../airfoil/airfoil_database/fad06.dat | 80 +++ .../airfoil/airfoil_database/fad07.dat | 82 +++ .../airfoil/airfoil_database/fad13.dat | 80 +++ .../airfoil/airfoil_database/fad14.dat | 80 +++ .../airfoil/airfoil_database/fad15.dat | 83 +++ .../airfoil/airfoil_database/fad16.dat | 82 +++ .../airfoil/airfoil_database/fad17.dat | 85 +++ .../airfoil/airfoil_database/fad18.dat | 80 +++ .../airfoil/airfoil_database/fad21.dat | 80 +++ .../airfoil/airfoil_database/fad23.dat | 80 +++ .../airfoil/airfoil_database/fad24.dat | 80 +++ .../airfoil/airfoil_database/hg41.dat | 141 +++++ .../airfoil/airfoil_database/hg42.dat | 141 +++++ .../airfoil/airfoil_database/hg43.dat | 141 +++++ .../airfoil/airfoil_database/hm1001.dat | 499 ++++++++++++++++++ .../airfoil/airfoil_database/hm391-2.dat | 495 +++++++++++++++++ .../airfoil/airfoil_database/hm391a.dat | 495 +++++++++++++++++ .../airfoil/airfoil_database/hm50t.dat | 495 +++++++++++++++++ .../airfoil/airfoil_database/hm51.dat | 171 ++++++ .../airfoil/airfoil_database/hm55.dat | 499 ++++++++++++++++++ .../airfoil/airfoil_database/hm56.dat | 498 +++++++++++++++++ .../airfoil/airfoil_database/hn003.dat | 114 ++++ .../airfoil/airfoil_database/hn032.dat | 114 ++++ .../airfoil/airfoil_database/hn033.dat | 114 ++++ .../airfoil/airfoil_database/hn034.dat | 114 ++++ .../airfoil/airfoil_database/hn035.dat | 115 ++++ .../airfoil/airfoil_database/hn036.dat | 114 ++++ .../airfoil/airfoil_database/hn038.dat | 114 ++++ .../airfoil/airfoil_database/hn1004.dat | 102 ++++ .../airfoil/airfoil_database/hn1015.dat | 102 ++++ .../airfoil/airfoil_database/hn1023.dat | 114 ++++ .../airfoil/airfoil_database/hn1027.dat | 114 ++++ .../airfoil/airfoil_database/hn1029.dat | 114 ++++ .../airfoil/airfoil_database/hn1032.dat | 102 ++++ .../airfoil/airfoil_database/hn1033.dat | 114 ++++ .../airfoil/airfoil_database/hn1033a.dat | 114 ++++ .../airfoil/airfoil_database/hn1036.dat | 114 ++++ .../airfoil/airfoil_database/hn1038.dat | 114 ++++ .../airfoil/airfoil_database/hn1051.dat | 114 ++++ .../airfoil/airfoil_database/hn1054.dat | 114 ++++ .../airfoil/airfoil_database/hn1069.dat | 102 ++++ .../airfoil/airfoil_database/hn1069a.dat | 102 ++++ .../airfoil/airfoil_database/hn1069b.dat | 102 ++++ .../airfoil/airfoil_database/hn1069c.dat | 102 ++++ .../airfoil/airfoil_database/hn1070.dat | 115 ++++ .../airfoil/airfoil_database/hn1091.dat | 102 ++++ .../airfoil/airfoil_database/hn1091a.dat | 102 ++++ .../airfoil/airfoil_database/hn1091b.dat | 102 ++++ .../airfoil/airfoil_database/hn153s.dat | 114 ++++ .../airfoil/airfoil_database/hn163.dat | 114 ++++ .../airfoil/airfoil_database/hn163ta.dat | 115 ++++ .../airfoil/airfoil_database/hn163tb.dat | 114 ++++ .../airfoil/airfoil_database/hn184.dat | 114 ++++ .../airfoil/airfoil_database/hn184m.dat | 114 ++++ .../airfoil/airfoil_database/hn188.dat | 114 ++++ .../airfoil/airfoil_database/hn203.dat | 114 ++++ .../airfoil/airfoil_database/hn211.dat | 114 ++++ .../airfoil/airfoil_database/hn216.dat | 114 ++++ .../airfoil/airfoil_database/hn216ta.dat | 114 ++++ .../airfoil/airfoil_database/hn217.dat | 115 ++++ .../airfoil/airfoil_database/hn227.dat | 114 ++++ .../airfoil/airfoil_database/hn239.dat | 114 ++++ .../airfoil/airfoil_database/hn274s.dat | 114 ++++ .../airfoil/airfoil_database/hn275s.dat | 114 ++++ .../airfoil/airfoil_database/hn276sa.dat | 114 ++++ .../airfoil/airfoil_database/hn304.dat | 114 ++++ .../airfoil/airfoil_database/hn304ta.dat | 114 ++++ .../airfoil/airfoil_database/hn309.dat | 114 ++++ .../airfoil/airfoil_database/hn30s.dat | 102 ++++ .../airfoil/airfoil_database/hn311s.dat | 114 ++++ .../airfoil/airfoil_database/hn312s.dat | 114 ++++ .../airfoil/airfoil_database/hn315s.dat | 74 +++ .../airfoil/airfoil_database/hn316s.dat | 74 +++ .../airfoil/airfoil_database/hn319.dat | 114 ++++ .../airfoil/airfoil_database/hn321.dat | 114 ++++ .../airfoil/airfoil_database/hn326.dat | 114 ++++ .../airfoil/airfoil_database/hn327.dat | 114 ++++ .../airfoil/airfoil_database/hn333.dat | 114 ++++ .../airfoil/airfoil_database/hn33s.dat | 102 ++++ .../airfoil/airfoil_database/hn350.dat | 114 ++++ .../airfoil/airfoil_database/hn350m01.dat | 114 ++++ .../airfoil/airfoil_database/hn350m02.dat | 114 ++++ .../airfoil/airfoil_database/hn352.dat | 114 ++++ .../airfoil/airfoil_database/hn354.dat | 114 ++++ .../airfoil/airfoil_database/hn354a.dat | 114 ++++ .../airfoil/airfoil_database/hn354e.dat | 114 ++++ .../airfoil/airfoil_database/hn354es.dat | 102 ++++ .../airfoil/airfoil_database/hn354oc.dat | 114 ++++ .../airfoil/airfoil_database/hn354sm.dat | 114 ++++ .../airfoil/airfoil_database/hn354sr.dat | 102 ++++ .../airfoil/airfoil_database/hn360.dat | 114 ++++ .../airfoil/airfoil_database/hn409.dat | 114 ++++ .../airfoil/airfoil_database/hn411.dat | 114 ++++ .../airfoil/airfoil_database/hn417.dat | 114 ++++ .../airfoil/airfoil_database/hn418.dat | 114 ++++ .../airfoil/airfoil_database/hn419.dat | 114 ++++ .../airfoil/airfoil_database/hn424.dat | 114 ++++ .../airfoil/airfoil_database/hn436.dat | 114 ++++ .../airfoil/airfoil_database/hn446.dat | 114 ++++ .../airfoil/airfoil_database/hn450.dat | 114 ++++ .../airfoil/airfoil_database/hn450s.dat | 114 ++++ .../airfoil/airfoil_database/hn452.dat | 102 ++++ .../airfoil/airfoil_database/hn456.dat | 102 ++++ .../airfoil/airfoil_database/hn462.dat | 114 ++++ .../airfoil/airfoil_database/hn464.dat | 114 ++++ .../airfoil/airfoil_database/hn465.dat | 114 ++++ .../airfoil/airfoil_database/hn470s.dat | 102 ++++ .../airfoil/airfoil_database/hn477s.dat | 102 ++++ .../airfoil/airfoil_database/hn478s.dat | 102 ++++ .../airfoil/airfoil_database/hn480.dat | 102 ++++ .../airfoil/airfoil_database/hn483.dat | 102 ++++ .../airfoil/airfoil_database/hn484.dat | 102 ++++ .../airfoil/airfoil_database/hn507.dat | 136 +++++ .../airfoil/airfoil_database/hn707.dat | 102 ++++ .../airfoil/airfoil_database/hn785.dat | 114 ++++ .../airfoil/airfoil_database/hn785sr.dat | 114 ++++ .../airfoil/airfoil_database/hn801.dat | 114 ++++ .../airfoil/airfoil_database/hn802.dat | 102 ++++ .../airfoil/airfoil_database/hn803.dat | 102 ++++ .../airfoil/airfoil_database/hn805.dat | 114 ++++ .../airfoil/airfoil_database/hn808.dat | 114 ++++ .../airfoil/airfoil_database/hn832.dat | 114 ++++ .../airfoil/airfoil_database/hn832ta.dat | 114 ++++ .../airfoil/airfoil_database/hn838.dat | 102 ++++ .../airfoil/airfoil_database/hn839d.dat | 102 ++++ .../airfoil/airfoil_database/hn840s.dat | 102 ++++ .../airfoil/airfoil_database/hn951.dat | 114 ++++ .../airfoil/airfoil_database/hn955.dat | 102 ++++ .../airfoil/airfoil_database/hn956.dat | 114 ++++ .../airfoil/airfoil_database/hn959.dat | 102 ++++ .../airfoil/airfoil_database/hn961sa.dat | 114 ++++ .../airfoil/airfoil_database/hn968s.dat | 102 ++++ .../airfoil/airfoil_database/hn969.dat | 102 ++++ .../airfoil/airfoil_database/hn971.dat | 114 ++++ .../airfoil/airfoil_database/hn972.dat | 114 ++++ .../airfoil/airfoil_database/hn973.dat | 114 ++++ .../airfoil/airfoil_database/hn974.dat | 102 ++++ .../airfoil/airfoil_database/hn975.dat | 102 ++++ .../airfoil/airfoil_database/hn975ta.dat | 102 ++++ .../airfoil/airfoil_database/hn976s.dat | 102 ++++ .../airfoil/airfoil_database/hn978.dat | 102 ++++ .../airfoil/airfoil_database/hn979.dat | 114 ++++ .../airfoil/airfoil_database/hn979d.dat | 114 ++++ .../airfoil/airfoil_database/hn980.dat | 102 ++++ .../airfoil/airfoil_database/hn981.dat | 102 ++++ .../airfoil/airfoil_database/hn984.dat | 102 ++++ .../airfoil/airfoil_database/hn989.dat | 102 ++++ .../airfoil/airfoil_database/hn990.dat | 102 ++++ .../airfoil/airfoil_database/hn997a.dat | 114 ++++ .../airfoil/airfoil_database/hn997b.dat | 114 ++++ .../airfoil/airfoil_database/hn998.dat | 114 ++++ .../airfoil/airfoil_database/hn999.dat | 114 ++++ .../airfoil/airfoil_database/hs179.dat | 57 ++ .../airfoil/airfoil_database/hs2080.dat | 69 +++ .../airfoil/airfoil_database/hs3080.dat | 44 ++ .../airfoil/airfoil_database/hs3090.dat | 44 ++ .../airfoil/airfoil_database/hs3412b.dat | 66 +++ .../airfoil/airfoil_database/hs3512.dat | 44 ++ .../airfoil/airfoil_database/hs510.dat | 61 +++ .../airfoil/airfoil_database/hs520.dat | 68 +++ .../airfoil/airfoil_database/hs522.dat | 71 +++ .../airfoil/airfoil_database/hs602.dat | 64 +++ .../airfoil/airfoil_database/jwl029.dat | 62 +++ .../airfoil/airfoil_database/jwl030.dat | 62 +++ .../airfoil/airfoil_database/jwl031.dat | 62 +++ .../airfoil/airfoil_database/jwl041.dat | 62 +++ .../airfoil/airfoil_database/jwl042.dat | 63 +++ .../airfoil/airfoil_database/jwl043.dat | 63 +++ .../airfoil/airfoil_database/jwl044.dat | 62 +++ .../airfoil/airfoil_database/jwl045.dat | 62 +++ .../airfoil/airfoil_database/jwl046.dat | 62 +++ .../airfoil/airfoil_database/jwl065.dat | 62 +++ .../airfoil/airfoil_database/jwl066.dat | 62 +++ .../airfoil/airfoil_database/jwl067.dat | 63 +++ .../airfoil/airfoil_database/jwl068.dat | 63 +++ .../airfoil/airfoil_database/jwl069.dat | 63 +++ .../airfoil/airfoil_database/jwl074.dat | 62 +++ .../airfoil/airfoil_database/jwl075.dat | 62 +++ .../airfoil/airfoil_database/jwl076.dat | 62 +++ .../airfoil/airfoil_database/jwl077.dat | 62 +++ .../airfoil/airfoil_database/jwl078.dat | 62 +++ .../airfoil/airfoil_database/jwl079.dat | 62 +++ .../airfoil/airfoil_database/jwl080.dat | 62 +++ .../airfoil/airfoil_database/jwl081.dat | 62 +++ .../airfoil/airfoil_database/jwl097.dat | 62 +++ .../airfoil/airfoil_database/jwl106.dat | 67 +++ .../airfoil/airfoil_database/m7372.dat | 142 +++++ .../geometry/airfoil/airfoil_database/m77.dat | 147 ++++++ .../airfoil/airfoil_database/mb7136rev.dat | 222 ++++++++ .../airfoil/airfoil_database/mb714rev.dat | 232 ++++++++ .../airfoil/airfoil_database/mc813rev.dat | 231 ++++++++ .../airfoil/airfoil_database/md8135rev.dat | 229 ++++++++ .../airfoil/airfoil_database/md814rev.dat | 232 ++++++++ .../airfoil/airfoil_database/mg05.dat | 108 ++++ .../airfoil/airfoil_database/mg05na09_210.dat | 92 ++++ .../airfoil/airfoil_database/mg06.dat | 74 +++ .../airfoil/airfoil_database/mg08.dat | 65 +++ .../airfoil/airfoil_database/mh126.dat | 64 +++ .../airfoil/airfoil_database/mh16.dat | 132 +++++ .../airfoil/airfoil_database/mh17.dat | 152 ++++++ .../airfoil/airfoil_database/mh18b.dat | 68 +++ .../airfoil/airfoil_database/mh31.dat | 70 +++ .../airfoil/airfoil_database/mh33.dat | 72 +++ .../airfoil/airfoil_database/mh34.dat | 73 +++ .../airfoil/airfoil_database/mh50.dat | 265 ++++++++++ .../airfoil/airfoil_database/mh51.dat | 266 ++++++++++ .../airfoil/airfoil_database/mh52.dat | 266 ++++++++++ .../airfoil/airfoil_database/mh53.dat | 267 ++++++++++ .../airfoil/airfoil_database/mh54.dat | 265 ++++++++++ .../airfoil/airfoil_database/mid010.dat | 141 +++++ .../airfoil/airfoil_database/mid011-3.dat | 201 +++++++ .../airfoil/airfoil_database/mid011-4.dat | 201 +++++++ .../airfoil/airfoil_database/mid011body.dat | 201 +++++++ .../airfoil/airfoil_database/mid012.dat | 201 +++++++ .../airfoil/airfoil_database/mid012r.dat | 201 +++++++ .../airfoil/airfoil_database/mid013.dat | 201 +++++++ .../airfoil/airfoil_database/mid015.dat | 141 +++++ .../airfoil/airfoil_database/mid020.dat | 101 ++++ .../airfoil/airfoil_database/mid021.dat | 129 +++++ .../airfoil/airfoil_database/mid022.dat | 131 +++++ .../airfoil/airfoil_database/mid027.dat | 218 ++++++++ .../airfoil/airfoil_database/mid029.dat | 161 ++++++ .../airfoil/airfoil_database/mid101.dat | 144 +++++ .../airfoil/airfoil_database/mid101tip.dat | 144 +++++ .../airfoil/airfoil_database/mid102.dat | 201 +++++++ .../airfoil/airfoil_database/mid102tip.dat | 201 +++++++ .../airfoil/airfoil_database/mid103.dat | 232 ++++++++ .../airfoil/airfoil_database/mid103bc45.dat | 204 +++++++ .../airfoil/airfoil_database/mid103c3.dat | 204 +++++++ .../airfoil/airfoil_database/mid104.dat | 209 ++++++++ .../airfoil/airfoil_database/mid105.dat | 205 +++++++ .../airfoil/airfoil_database/mid106.dat | 263 +++++++++ .../airfoil/airfoil_database/mid107.dat | 230 ++++++++ .../airfoil/airfoil_database/mid108a.dat | 206 ++++++++ .../airfoil/airfoil_database/mid108b.dat | 206 ++++++++ .../airfoil/airfoil_database/mid110.dat | 161 ++++++ .../airfoil/airfoil_database/mid111.dat | 161 ++++++ .../airfoil/airfoil_database/mid112.dat | 161 ++++++ .../airfoil/airfoil_database/mid113.dat | 103 ++++ .../airfoil/airfoil_database/mid114.dat | 103 ++++ .../airfoil/airfoil_database/mid115-7.dat | 141 +++++ .../airfoil/airfoil_database/mid115.dat | 161 ++++++ .../airfoil/airfoil_database/mid116.dat | 161 ++++++ .../airfoil/airfoil_database/mid117.dat | 143 +++++ .../airfoil/airfoil_database/mid118.dat | 149 ++++++ .../airfoil/airfoil_database/mid120.dat | 161 ++++++ .../airfoil/airfoil_database/mid122.dat | 161 ++++++ .../airfoil/airfoil_database/mid151a.dat | 203 +++++++ .../airfoil/airfoil_database/mid151b.dat | 203 +++++++ .../airfoil/airfoil_database/mid151c.dat | 203 +++++++ .../airfoil/airfoil_database/mid153a.dat | 203 +++++++ .../airfoil/airfoil_database/mid153b.dat | 203 +++++++ .../airfoil/airfoil_database/mid153c.dat | 203 +++++++ .../airfoil/airfoil_database/mid173c.dat | 161 ++++++ .../airfoil/airfoil_database/mid304.dat | 142 +++++ .../airfoil/airfoil_database/mid309.dat | 143 +++++ .../airfoil/airfoil_database/mid311.dat | 143 +++++ .../airfoil_database/mid31_F3J_F5J.dat | 141 +++++ .../airfoil/airfoil_database/mid321a.dat | 148 ++++++ .../airfoil/airfoil_database/mid321b.dat | 148 ++++++ .../airfoil/airfoil_database/mid321c.dat | 148 ++++++ .../airfoil/airfoil_database/mid321d.dat | 141 +++++ .../airfoil/airfoil_database/mid321e.dat | 141 +++++ .../airfoil/airfoil_database/mid322.dat | 141 +++++ .../airfoil/airfoil_database/mid327-12.dat | 203 +++++++ .../airfoil/airfoil_database/mid327-15.dat | 203 +++++++ .../airfoil/airfoil_database/mid327-18.dat | 203 +++++++ .../airfoil/airfoil_database/mid327.dat | 223 ++++++++ .../airfoil_database/mid32_F3J_F5J.dat | 161 ++++++ .../airfoil_database/mid33_F3J_F5J.dat | 141 +++++ .../airfoil/airfoil_database/mid343.dat | 141 +++++ .../airfoil_database/mid34_F3J_F5J.dat | 141 +++++ .../airfoil/airfoil_database/mid36_F5Js.dat | 143 +++++ .../airfoil/airfoil_database/mid371.dat | 160 ++++++ .../airfoil/airfoil_database/mid371aw.dat | 160 ++++++ .../airfoil/airfoil_database/mid37_F5Js.dat | 142 +++++ .../airfoil/airfoil_database/mid38_F5Js.dat | 141 +++++ .../airfoil/airfoil_database/mid393.dat | 145 +++++ .../airfoil/airfoil_database/mid393ul25.dat | 141 +++++ .../airfoil/airfoil_database/mid39_F5Js.dat | 142 +++++ .../airfoil/airfoil_database/mid403.dat | 141 +++++ .../airfoil/airfoil_database/mid405e.dat | 141 +++++ .../airfoil/airfoil_database/mid405w2.dat | 145 +++++ .../airfoil/airfoil_database/mid406w2.dat | 145 +++++ .../airfoil/airfoil_database/mid415.dat | 151 ++++++ .../airfoil/airfoil_database/mid44a.dat | 142 +++++ .../airfoil/airfoil_database/mid44b.dat | 161 ++++++ .../airfoil/airfoil_database/mid44c.dat | 161 ++++++ .../airfoil/airfoil_database/mid44d.dat | 143 +++++ .../airfoil/airfoil_database/mid44e.dat | 142 +++++ .../airfoil/airfoil_database/mid455.dat | 262 +++++++++ .../airfoil/airfoil_database/mid97f.dat | 241 +++++++++ .../airfoil/airfoil_database/mid97n.dat | 241 +++++++++ .../airfoil/airfoil_database/midh2a.dat | 142 +++++ .../airfoil/airfoil_database/midh2b.dat | 141 +++++ .../airfoil/airfoil_database/midh2d.dat | 182 +++++++ .../airfoil/airfoil_database/mjp711f3rev.dat | 225 ++++++++ .../airfoil/airfoil_database/mjp712rev.dat | 217 ++++++++ .../airfoil/airfoil_database/mjz1211.dat | 258 +++++++++ .../airfoil/airfoil_database/mrv120.dat | 100 ++++ .../airfoil/airfoil_database/ms19_87.dat | 78 +++ .../airfoil/airfoil_database/ms2511gpv.dat | 143 +++++ .../airfoil/airfoil_database/ms2513gpv.dat | 143 +++++ .../airfoil/airfoil_database/ms2515gpv.dat | 143 +++++ .../airfoil/airfoil_database/ms2_95.dat | 78 +++ .../airfoil/airfoil_database/ms311gpv.dat | 143 +++++ .../airfoil/airfoil_database/ms313gpv.dat | 143 +++++ .../airfoil/airfoil_database/ms315gpv.dat | 143 +++++ .../airfoil/airfoil_database/ms33_11gp.dat | 141 +++++ .../airfoil/airfoil_database/ms33_11gpt.dat | 141 +++++ .../airfoil/airfoil_database/ms33_13gp.dat | 141 +++++ .../airfoil/airfoil_database/ms33_15gp.dat | 141 +++++ .../airfoil/airfoil_database/ms535-1.dat | 141 +++++ .../airfoil/airfoil_database/ms535-2.dat | 141 +++++ .../airfoil/airfoil_database/ms535-3v.dat | 141 +++++ .../airfoil/airfoil_database/msa812rev.dat | 231 ++++++++ .../airfoil/airfoil_database/mu8.5_1.73.dat | 148 ++++++ .../airfoil/airfoil_database/mve8516.dat | 141 +++++ .../airfoil/airfoil_database/mve8516f3.dat | 144 +++++ .../airfoil/airfoil_database/mvr22_3-10.dat | 100 ++++ .../airfoil/airfoil_database/n64212rb.dat | 63 +++ .../airfoil/airfoil_database/nacak6e.dat | 58 ++ .../airfoil/airfoil_database/nacak6m.dat | 54 ++ .../airfoil/airfoil_database/nacak6s.dat | 52 ++ .../airfoil_database/nm-classic-saumon.dat | 269 ++++++++++ .../airfoil/airfoil_database/nm-classic.dat | 265 ++++++++++ .../airfoil/airfoil_database/nm-retro-13.dat | 263 +++++++++ .../airfoil/airfoil_database/nm-retro-14.dat | 263 +++++++++ .../nm-retro-16-emplanture.dat | 263 +++++++++ .../airfoil_database/nm-retro-saumon-30.dat | 64 +++ .../airfoil_database/nm-retro-saumon-50.dat | 64 +++ .../airfoil/airfoil_database/nm-spatz-13.dat | 63 +++ .../airfoil/airfoil_database/nm-spatz-14.dat | 63 +++ .../airfoil_database/nm-spatz-saumon-30.dat | 63 +++ .../airfoil_database/nm-spatz-saumon-50.dat | 63 +++ .../airfoil/airfoil_database/nm0160inches.dat | 263 +++++++++ .../airfoil/airfoil_database/nm02f3f.dat | 263 +++++++++ .../airfoil/airfoil_database/nm08.dat | 263 +++++++++ .../airfoil/airfoil_database/nm09.dat | 153 ++++++ .../airfoil/airfoil_database/nm10.dat | 263 +++++++++ .../airfoil/airfoil_database/nm12f3f.dat | 267 ++++++++++ .../airfoil/airfoil_database/nm18-s.dat | 269 ++++++++++ .../airfoil/airfoil_database/nm18.dat | 267 ++++++++++ .../airfoil/airfoil_database/nm19-s.dat | 269 ++++++++++ .../airfoil/airfoil_database/nm19.dat | 267 ++++++++++ .../airfoil/airfoil_database/nm20-s.dat | 155 ++++++ .../airfoil/airfoil_database/nm20.dat | 267 ++++++++++ .../airfoil/airfoil_database/nm23.dat | 267 ++++++++++ .../airfoil_database/nm26-1-23smoothed.dat | 261 +++++++++ .../airfoil_database/nm26-2smoothed.dat | 264 +++++++++ .../airfoil_database/nm26-3smoothed.dat | 263 +++++++++ .../airfoil/airfoil_database/nm28.dat | 82 +++ .../airfoil/airfoil_database/nm29.dat | 264 +++++++++ .../airfoil/airfoil_database/nm32-s.dat | 153 ++++++ .../airfoil/airfoil_database/nm32.dat | 153 ++++++ .../airfoil/airfoil_database/nm41-2f3j.dat | 175 ++++++ .../airfoil/airfoil_database/nm41-3f3j.dat | 175 ++++++ .../airfoil/airfoil_database/nm41f3j.dat | 154 ++++++ .../airfoil/airfoil_database/nmr13.dat | 100 ++++ .../airfoil/airfoil_database/nn1817.dat | 76 +++ .../airfoil/airfoil_database/pegase.dat | 107 ++++ .../airfoil/airfoil_database/phoenix.dat | 91 ++++ .../airfoil/airfoil_database/phonix10.dat | 497 +++++++++++++++++ .../airfoil/airfoil_database/r23010.dat | 62 +++ .../airfoil/airfoil_database/rb951014.dat | 64 +++ .../airfoil/airfoil_database/rhodesg34r.dat | 103 ++++ .../airfoil/airfoil_database/rk40.dat | 67 +++ .../airfoil/airfoil_database/rs001m60.dat | 104 ++++ .../airfoil/airfoil_database/rs001m75.dat | 104 ++++ .../airfoil/airfoil_database/salazV3_emp.dat | 141 +++++ .../airfoil/airfoil_database/salazV3_ext.dat | 141 +++++ .../airfoil/airfoil_database/salaz_emp.dat | 144 +++++ .../airfoil/airfoil_database/salaz_moy.dat | 144 +++++ .../airfoil/airfoil_database/sb95_105_2.dat | 62 +++ .../airfoil/airfoil_database/sb95_115_2.dat | 62 +++ .../airfoil/airfoil_database/sb95_95_2.dat | 62 +++ .../airfoil/airfoil_database/sb96_105_3.dat | 62 +++ .../airfoil/airfoil_database/sb96_116_3.dat | 62 +++ .../airfoil/airfoil_database/sb96_127_3.dat | 62 +++ .../airfoil/airfoil_database/sb96_lm.dat | 62 +++ .../airfoil/airfoil_database/sb96_mu.dat | 62 +++ .../airfoil/airfoil_database/sb96d_13_3.dat | 63 +++ .../airfoil/airfoil_database/sb97_8_125.dat | 61 +++ .../airfoil/airfoil_database/sb97_fw.dat | 62 +++ .../airfoil/airfoil_database/sb98vm5.dat | 63 +++ 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262 +++++++++ .../airfoil/airfoil_database/tp202-9.dat | 261 +++++++++ .../airfoil/airfoil_database/tp204.dat | 262 +++++++++ .../airfoil/airfoil_database/tp210-10.dat | 261 +++++++++ .../airfoil/airfoil_database/tp210-11.dat | 261 +++++++++ .../airfoil/airfoil_database/tp28-0.dat | 261 +++++++++ .../airfoil/airfoil_database/tp28-4.dat | 260 +++++++++ .../airfoil/airfoil_database/tp28-60.dat | 261 +++++++++ .../airfoil/airfoil_database/tp28-l.dat | 260 +++++++++ .../airfoil/airfoil_database/tp28-m.dat | 259 +++++++++ .../airfoil/airfoil_database/tp28-s.dat | 259 +++++++++ .../airfoil/airfoil_database/tp29-5.dat | 264 +++++++++ .../airfoil/airfoil_database/tp29-6.dat | 264 +++++++++ .../airfoil/airfoil_database/tp29-7.dat | 264 +++++++++ .../airfoil/airfoil_database/tp29-8.dat | 264 +++++++++ .../airfoil/airfoil_database/tp29-85.dat | 262 +++++++++ .../airfoil/airfoil_database/tp29-9.dat | 264 +++++++++ .../airfoil_database/tp36-95-tp29-85.dat | 263 +++++++++ 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.../airfoil/airfoil_database/wsm825.dat | 264 +++++++++ 518 files changed, 77104 insertions(+) create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/AV-1.7-8.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/BE5030FVNC2t.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/BE5045FVNC2t.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/BE5655FVNC2t.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/DP1,68-8,37_DS.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/DP1,72-8,16_DS.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/DP1,72-8,32_DS.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/DP1,77-8,23_DS.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/DP1,79-8,37_DS.dat create mode 100644 aerosandbox/geometry/airfoil/airfoil_database/DP1,82-8,21_DS.dat create mode 100644 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C'est avec lui que j'ai gagné le premier concours F3F de Vernègues 2007 dans la catégorie 60". Il est prévu pour des volets de coubures full span 29% inclinable à -3° pour accélérer et +3° pour grimper et snap flap. Il est possible de le charger assez lourdement sans dégrader les qualitées de vol à basse vitesse. + Le profil AVX est le fruit de nombreux essais en vols, il fait pour voler vite et gratter si le vent faiblit subittement. +jf.sarteur _ AT _ tele2 POINT fr \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/az2007_emp.dat b/aerosandbox/geometry/airfoil/airfoil_database/az2007_emp.dat new file mode 100644 index 00000000..a7815fc9 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/az2007_emp.dat @@ -0,0 +1,143 @@ +az2007_8._1.4%_emplanture + 1.00000 0.00029 + 0.99134 0.00005 + 0.97642 0.00003 + 0.96136 0.00036 + 0.94625 0.00101 + 0.93111 0.00189 + 0.91595 0.00295 + 0.90077 0.00412 + 0.88560 0.00539 + 0.87042 0.00671 + 0.85524 0.00813 + 0.84007 0.00959 + 0.82490 0.01110 + 0.80974 0.01264 + 0.79457 0.01424 + 0.77939 0.01583 + 0.76421 0.01742 + 0.74903 0.01905 + 0.73387 0.02070 + 0.71869 0.02233 + 0.70351 0.02396 + 0.68834 0.02560 + 0.67316 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new file mode 100644 index 00000000..fa7f872d --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/cb2513.dat @@ -0,0 +1,45 @@ +CB2513 (c)ch.baron + 1.00000 0.00000 + 0.99000 0.00245 + 0.95000 0.01000 + 0.90000 0.02015 + 0.85000 0.03077 + 0.80000 0.04107 + 0.70000 0.05915 + 0.60000 0.07314 + 0.50000 0.08290 + 0.40000 0.08816 + 0.35000 0.08900 + 0.30000 0.08832 + 0.25000 0.08593 + 0.20000 0.08143 + 0.15000 0.07409 + 0.10000 0.06263 + 0.05000 0.04418 + 0.02500 0.02981 + 0.01250 0.01962 + 0.00500 0.01106 + 0.00200 0.00625 + 0.00000 0.00000 + 0.00200 -0.00633 + 0.00500 -0.01039 + 0.01250 -0.01608 + 0.02500 -0.02191 + 0.05000 -0.02928 + 0.10000 -0.03722 + 0.15000 -0.04089 + 0.20000 -0.04236 + 0.25000 -0.04251 + 0.30000 -0.04168 + 0.35000 -0.04024 + 0.40000 -0.03835 + 0.50000 -0.03339 + 0.60000 -0.02727 + 0.70000 -0.02012 + 0.80000 -0.01237 + 0.85000 -0.00851 + 0.90000 -0.00492 + 0.95000 -0.00210 + 0.99000 -0.00063 + 1.00000 0.00000 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+0.5 0.108857143 +0.45 0.112285714 +0.4 0.113428571 +0.35 0.112 +0.3 0.108857143 +0.25 0.103428571 +0.2 0.094571429 +0.15 0.082 +0.1 0.067714286 +0.05 0.044571429 +0.01 0.016 +0.000000 0.000000 + 0.010000 -0.010571 + 0.050000 -0.023143 + 0.100000 -0.032286 + 0.150000 -0.035714 + 0.200000 -0.037429 + 0.250000 -0.039143 + 0.300000 -0.042000 + 0.350000 -0.042857 + 0.400000 -0.043429 + 0.450000 -0.042857 + 0.500000 -0.042000 +0.55 -0.039142857 +0.6 -0.037428571 +0.65 -0.032857143 +0.7 -0.028571429 +0.75 -0.021428571 +0.8 -0.014285714 +0.85 -0.005142857 +0.9 0.000857143 +0.95 0.003142857 +1 0 + +le profil du cristal je l'ai bien trouvé dans une revue modéliste (RCM je crois) +"COUSIN ERIC" \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/dp189-7831.dat b/aerosandbox/geometry/airfoil/airfoil_database/dp189-7831.dat new file mode 100644 index 00000000..0c76161d --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/dp189-7831.dat @@ -0,0 +1,93 @@ +DP 1.89/7.83 (c)"Dirk Pflug" + 1.00000 0.00000 + 0.98630 0.00153 + 0.95899 0.00454 + 0.93079 0.00761 + 0.90261 0.01062 + 0.87438 0.01360 + 0.84612 0.01652 + 0.81787 0.01939 + 0.78963 0.02222 + 0.76142 0.02499 + 0.73334 0.02769 + 0.70525 0.03036 + 0.67702 0.03299 + 0.64878 0.03556 + 0.62056 0.03809 + 0.59244 0.04056 + 0.56419 0.04299 + 0.53585 0.04538 + 0.50764 0.04763 + 0.47940 0.04968 + 0.45126 0.05153 + 0.42338 0.05315 + 0.39519 0.05452 + 0.36697 0.05568 + 0.33879 0.05659 + 0.31064 0.05724 + 0.28251 0.05755 + 0.25447 0.05749 + 0.22654 0.05698 + 0.19872 0.05593 + 0.17108 0.05428 + 0.14372 0.05188 + 0.11672 0.04856 + 0.09032 0.04412 + 0.06481 0.03828 + 0.04102 0.03071 + 0.02093 0.02160 + 0.00845 0.01306 + 0.00289 0.00710 + 0.00060 0.00288 + 0.00000 0.00000 + 0.00180 -0.00335 + 0.00619 -0.00633 + 0.01528 -0.00990 + 0.03385 -0.01406 + 0.05920 -0.01740 + 0.08618 -0.01952 + 0.11376 -0.02078 + 0.14167 -0.02144 + 0.16976 -0.02167 + 0.19796 -0.02156 + 0.22621 -0.02122 + 0.25426 -0.02072 + 0.28244 -0.02006 + 0.31057 -0.01931 + 0.33882 -0.01842 + 0.36680 -0.01745 + 0.39489 -0.01645 + 0.42320 -0.01545 + 0.45155 -0.01443 + 0.47988 -0.01336 + 0.50822 -0.01224 + 0.53651 -0.01104 + 0.56480 -0.00982 + 0.59313 -0.00853 + 0.62129 -0.00718 + 0.64960 -0.00585 + 0.67791 -0.00461 + 0.70610 -0.00341 + 0.73424 -0.00219 + 0.76249 -0.00100 + 0.79080 0.00004 + 0.81911 0.00094 + 0.84739 0.00172 + 0.87559 0.00226 + 0.90369 0.00250 + 0.93186 0.00237 + 0.95983 0.00196 + 0.98640 0.00090 + 1.00000 0.00000 + +The DP +1.89/7.83 is mainly for modelplans, especially soarer. It´s a very allround +profil, astonishly fast but creates also a lot of lift for floating an high +Cl for tight turns. It´s faster than the MG 06 and has better Cl/Cd. There +will be an article about this airfoil in german magazine "aufwind" in +2/2005 or 3/2005. I attached you the file in *.dat format. Heiner Fischer +who makes the famous estrella for F3B has made new moulds whith a different +DP-airfoil - coordinates will be secret - and decided just after one weekend +testing together with Reihard Liese to stop the production of the old +estrella with the MW 3 and to produce from now on only the estrella dp. + diff --git a/aerosandbox/geometry/airfoil/airfoil_database/ds19.dat b/aerosandbox/geometry/airfoil/airfoil_database/ds19.dat new file mode 100644 index 00000000..07cdff5b --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/ds19.dat @@ -0,0 +1,148 @@ +DS19 coords (c)Joe Wurts +1.000000 -0.000170 +0.993213 0.000857 +0.980310 0.002838 +0.965020 0.005130 +0.948589 0.007521 +0.931770 0.009903 +0.914825 0.012245 +0.897839 0.014535 +0.880837 0.016770 +0.863843 0.018945 +0.846859 0.021057 +0.829964 0.023097 +0.813302 0.025047 +0.797488 0.026946 +0.781115 0.029023 +0.764218 0.031099 +0.747249 0.033124 +0.730213 0.035096 +0.713174 0.037008 +0.696126 0.038857 +0.679066 0.040645 +0.662007 0.042372 +0.644941 0.044036 +0.627871 0.045636 +0.610798 0.047172 +0.593726 0.048642 +0.576648 0.050046 +0.559571 0.051384 +0.542499 0.052652 +0.525425 0.053849 +0.508357 0.054974 +0.491300 0.056024 +0.474251 0.056994 +0.457211 0.057883 +0.440186 0.058687 +0.423174 0.059401 +0.406173 0.060022 +0.389185 0.060548 +0.372216 0.060975 +0.355279 0.061297 +0.338384 0.061506 +0.321524 0.061594 +0.304713 0.061551 +0.287957 0.061370 +0.271252 0.061038 +0.254613 0.060547 +0.238051 0.059884 +0.221565 0.059036 +0.205166 0.057992 +0.188873 0.056739 +0.172703 0.055261 +0.156680 0.053542 +0.140822 0.051562 +0.125186 0.049307 +0.109810 0.046752 +0.094774 0.043879 +0.080176 0.040671 +0.066192 0.037132 +0.053100 0.033299 +0.041308 0.029292 +0.031285 0.025326 +0.023261 0.021621 +0.017090 0.018298 +0.012396 0.015366 +0.008806 0.012772 +0.006033 0.010439 +0.003888 0.008297 +0.002257 0.006280 +0.001087 0.004340 +0.000346 0.002458 +0.000023 0.000664 +0.000097 -0.001093 +0.000604 -0.002878 +0.001590 -0.004643 +0.003071 -0.006320 +0.005062 -0.007883 +0.007590 -0.009345 +0.010761 -0.010729 +0.014764 -0.012095 +0.019934 -0.013492 +0.026790 -0.014981 +0.035903 -0.016566 +0.047624 -0.018166 +0.061502 -0.019652 +0.076755 -0.020928 +0.092711 -0.021975 +0.109046 -0.022802 +0.125644 -0.023449 +0.142352 -0.023934 +0.159173 -0.024272 +0.176082 -0.024486 +0.193048 -0.0245831 +0.210093 -0.024583 +0.227176 -0.024497 +0.244283 -0.024327 +0.261478 -0.024089 +0.278650 -0.023795 +0.295838 -0.023434 +0.313105 -0.023023 +0.330324 -0.022570 +0.347575 -0.022062 +0.364859 -0.021514 +0.382170 -0.020936 +0.399432 -0.020321 +0.416747 -0.019667 +0.434068 -0.018987 +0.451391 -0.018279 +0.468744 -0.017547 +0.486074 -0.016795 +0.503427 -0.016016 +0.520816 -0.015223 +0.538178 -0.014420 +0.555537 -0.013597 +0.572909 -0.012758 +0.590272 -0.011916 +0.607601 -0.011068 +0.624945 -0.010206 +0.642301 -0.009342 +0.659669 -0.008470 +0.677041 -0.007596 +0.694432 -0.006712 +0.711844 -0.005829 +0.729251 -0.004944 +0.746622 -0.004063 +0.763921 -0.003194 +0.780985 -0.002355 +0.797461 -0.001531 +0.813704 -0.000987 +0.830665 -0.000485 +0.847818 -0.000012 +0.864958 0.000407 +0.882058 0.000762 +0.899076 0.001036 +0.916008 0.001213 +0.932815 0.001275 +0.949395 0.001203 +0.965513 0.000976 +0.980483 0.000601 +0.993183 0.000136 +1.000000 -0.000170 + +http://www.rcgroups.com/forums/showthread.php?t=309550 +Here are coords for the ds19 and ds21. + +The 19 is meant for lighter conditions. I originally designed it for Brian Mclean for the Extreme, which by Brians request, had performance rqmts for light condition slope flight. This drove the optimal performance to high Cl, low Re. The 21 is closely related, still good for fairly light air, but a bit better straight line performance. + +For extreme DS speeds, there are better airfoils. These were meant to fill Brians desires, and seem to have met his criteria fairly well. It would be fun to develop the ultimate DS machine, I've just not had the motivation yet to work on one yet. Just takes time and money... \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/ds21.dat b/aerosandbox/geometry/airfoil/airfoil_database/ds21.dat new file mode 100644 index 00000000..aefbe1d4 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/ds21.dat @@ -0,0 +1,265 @@ +DS 21 coords (c)Joe Wurts +1.000000 -0.000170 +0.999657 -0.000144 +0.999115 -0.000066 +0.998228 0.000061 +0.997004 0.000236 +0.995448 0.000459 +0.993565 0.000728 +0.991361 0.001044 +0.988839 0.001405 +0.986004 0.001809 +0.982862 0.002257 +0.979416 0.002746 +0.975669 0.003275 +0.971627 0.003841 +0.967293 0.004445 +0.962671 0.005084 +0.957765 0.005759 +0.952579 0.006466 +0.947116 0.007206 +0.941381 0.007977 +0.935380 0.008778 +0.929115 0.009608 +0.922593 0.010464 +0.915818 0.011348 +0.908794 0.012257 +0.901528 0.013188 +0.894023 0.014141 +0.886285 0.015115 +0.878319 0.016106 +0.870130 0.017113 +0.861721 0.018135 +0.853097 0.019170 +0.844263 0.020217 +0.835221 0.021271 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0.000580 +0.949120 0.000601 +0.954793 0.000602 +0.960147 0.000586 +0.965179 0.000555 +0.969882 0.000511 +0.974254 0.000456 +0.978289 0.000393 +0.981987 0.000326 +0.985342 0.000254 +0.988354 0.000182 +0.991019 0.000111 +0.993336 0.000045 +0.995304 -0.000016 +0.996921 -0.000069 +0.998186 -0.000112 +0.999096 -0.000143 +0.999650 -0.000163 +1.000000 -0.000170 + +http://www.rcgroups.com/forums/showthread.php?t=309550 +Here are coords for the ds19 and ds21. + +The 19 is meant for lighter conditions. I originally designed it for Brian Mclean for the Extreme, which by Brians request, had performance rqmts for light condition slope flight. This drove the optimal performance to high Cl, low Re. The 21 is closely related, still good for fairly light air, but a bit better straight line performance. + +For extreme DS speeds, there are better airfoils. These were meant to fill Brians desires, and seem to have met his criteria fairly well. It would be fun to develop the ultimate DS machine, I've just not had the motivation yet to work on one yet. Just takes time and money... \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/du06-w-200-selig.dat b/aerosandbox/geometry/airfoil/airfoil_database/du06-w-200-selig.dat new file mode 100644 index 00000000..734a1c92 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/du06-w-200-selig.dat @@ -0,0 +1,204 @@ +DU 06-W-200_VAWT_airfoil_modby Tracfoil + 1.000000 0.000330 + 0.995071 0.000991 + 0.988745 0.001790 + 0.980844 0.002821 + 0.971354 0.004134 + 0.960703 0.005676 + 0.949361 0.007380 + 0.937673 0.009188 + 0.925781 0.011064 + 0.913799 0.012967 + 0.901782 0.014892 + 0.889754 0.016828 + 0.877727 0.018779 + 0.865704 0.020741 + 0.853697 0.022719 + 0.841679 0.024714 + 0.829686 0.026717 + 0.817740 0.028741 + 0.805771 0.030796 + 0.793799 0.032857 + 0.781854 0.034939 + 0.769889 0.037053 + 0.757924 0.039180 + 0.746007 0.041327 + 0.734077 0.043511 + 0.722128 0.045716 + 0.710225 0.047936 + 0.698325 0.050176 + 0.686453 0.052417 + 0.674589 0.054685 + 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+0.79093 -0.01136 +0.81865 -0.01013 +0.84635 -0.00881 +0.87406 -0.00740 +0.90176 -0.00592 +0.92946 -0.00436 +0.95713 -0.00276 +0.98443 -0.00115 +1.00000 -0.00023 + +24/05/2013 (http://www.modelisme.com/forum/aero-ailes-volantes/123950-et-une-aile-sal-de-plus-la-cylon.html#post1190409) \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/fad17.dat b/aerosandbox/geometry/airfoil/airfoil_database/fad17.dat new file mode 100644 index 00000000..1ca67fe7 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/fad17.dat @@ -0,0 +1,85 @@ +FAD17 spécial aile volante 60 mousse (c)Franck.A +1.00000 0.00000 +0.97483 -0.00026 +0.94087 0.00094 +0.89963 0.00338 +0.85261 0.00679 +0.80131 0.01096 +0.74724 0.01562 +0.69192 0.02055 +0.63683 0.02550 +0.58350 0.03022 +0.53342 0.03449 +0.48750 0.03814 +0.44554 0.04118 +0.40716 0.04366 +0.37203 0.04560 +0.33980 0.04704 +0.31011 0.04800 +0.28261 0.04852 +0.25696 0.04863 +0.23279 0.04837 +0.20978 0.04776 +0.18776 0.04683 +0.16678 0.04560 +0.14689 0.04407 +0.12814 0.04227 +0.11057 0.04020 +0.09424 0.03789 +0.07919 0.03533 +0.06548 0.03256 +0.05315 0.02957 +0.04225 0.02640 +0.03275 0.02309 +0.02459 0.01971 +0.01771 0.01633 +0.01205 0.01302 +0.00755 0.00986 +0.00416 0.00690 +0.00181 0.00423 +0.00044 0.00190 +0.00000 0.00000 +0.00089 -0.00312 +0.00353 -0.00606 +0.00791 -0.00879 +0.01397 -0.01131 +0.02170 -0.01363 +0.03106 -0.01573 +0.04202 -0.01760 +0.05455 -0.01924 +0.06862 -0.02065 +0.08420 -0.02182 +0.10124 -0.02274 +0.11967 -0.02344 +0.13943 -0.02394 +0.16045 -0.02424 +0.18266 -0.02438 +0.20598 -0.02436 +0.23036 -0.02422 +0.25571 -0.02395 +0.28197 -0.02359 +0.30907 -0.02315 +0.33703 -0.02264 +0.36591 -0.02206 +0.39579 -0.02143 +0.42677 -0.02074 +0.45891 -0.02001 +0.49230 -0.01922 +0.52702 -0.01839 +0.56315 -0.01753 +0.60077 -0.01663 +0.63992 -0.01570 +0.68035 -0.01472 +0.72165 -0.01363 +0.76339 -0.01241 +0.80517 -0.01102 +0.84656 -0.00940 +0.88716 -0.00754 +0.92654 -0.00537 +0.96429 -0.00287 +1.00000 0.00000 + + +http://forum.modelisme.com/viewtopic.php?id=98794&p=2 +J'ai bossé un peu sur la question, et je vous propose un profil spécial aile volante 60 mousse. Il est un poil fin (7.3%), mais sa plage de Cz est très correcte (surtout pour une aile volante), et le gain en Cx sur une large plage est sympathique par rapport aux canons de la catégorie. Bien sûr, il est autostable (Cm0 = +0.012) "d'origine" +Ce profil sera plutôt à l'aise avec un peu plus d'allongement (environ 9, soit une surface de 25dm²) que la concurrence, et une charge alaire un peu plus faible (viser 25g/dm² à vide, soit 600g). \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/fad18.dat b/aerosandbox/geometry/airfoil/airfoil_database/fad18.dat new file mode 100644 index 00000000..6110cea5 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/fad18.dat @@ -0,0 +1,80 @@ +FAD18 (c)Franck.Aguerre Performances pour 60"et F3F à incidence intégrale +1.00000 0.00009 +0.92245 0.00777 +0.85304 0.01464 +0.79098 0.02076 +0.73548 0.02622 +0.68578 0.03112 +0.64106 0.03544 +0.60056 0.03924 +0.56348 0.04260 +0.52903 0.04556 +0.49644 0.04817 +0.46515 0.05049 +0.43502 0.05251 +0.40600 0.05423 +0.37801 0.05566 +0.35098 0.05679 +0.32484 0.05759 +0.29950 0.05807 +0.27491 0.05823 +0.25097 0.05803 +0.22763 0.05747 +0.20491 0.05654 +0.18290 0.05523 +0.16172 0.05352 +0.14150 0.05140 +0.12234 0.04889 +0.10438 0.04601 +0.08770 0.04281 +0.07244 0.03931 +0.05869 0.03560 +0.04657 0.03174 +0.03602 0.02778 +0.02698 0.02380 +0.01939 0.01983 +0.01316 0.01595 +0.00822 0.01220 +0.00453 0.00864 +0.00200 0.00537 +0.00050 0.00244 +0.00003 -0.00008 +0.00049 -0.00231 +0.00204 -0.00448 +0.00474 -0.00659 +0.00851 -0.00871 +0.01355 -0.01080 +0.02002 -0.01281 +0.02803 -0.01468 +0.03767 -0.01641 +0.04906 -0.01797 +0.06230 -0.01934 +0.07744 -0.02052 +0.09428 -0.02150 +0.11267 -0.02228 +0.13239 -0.02289 +0.15329 -0.02336 +0.17515 -0.02366 +0.19779 -0.02381 +0.22105 -0.02381 +0.24472 -0.02366 +0.26863 -0.02340 +0.29277 -0.02302 +0.31732 -0.02255 +0.34245 -0.02197 +0.36836 -0.02128 +0.39520 -0.02050 +0.42316 -0.01963 +0.45244 -0.01866 +0.48319 -0.01761 +0.51561 -0.01646 +0.54987 -0.01522 +0.58630 -0.01389 +0.62527 -0.01245 +0.66714 -0.01091 +0.71228 -0.00924 +0.76105 -0.00748 +0.81386 -0.00554 +0.87102 -0.00358 +0.93295 -0.00169 +1.00000 -0.00009 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/fad21.dat b/aerosandbox/geometry/airfoil/airfoil_database/fad21.dat new file mode 100644 index 00000000..737fc9f9 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/fad21.dat @@ -0,0 +1,80 @@ +FAD21 (c)Franck.Aguerre Pour avion et planeur de début +1.00000 0.00000 +0.98702 0.00170 +0.96050 0.00542 +0.93189 0.00984 +0.90192 0.01471 +0.87170 0.01967 +0.84194 0.02467 +0.81274 0.02980 +0.78148 0.03556 +0.75247 0.03997 +0.72226 0.04470 +0.69184 0.04942 +0.66154 0.05398 +0.63119 0.05839 +0.60082 0.06264 +0.57050 0.06674 +0.54025 0.07065 +0.51008 0.07434 +0.48001 0.07774 +0.44999 0.08080 +0.42002 0.08346 +0.39015 0.08568 +0.36029 0.08738 +0.33043 0.08852 +0.30058 0.08905 +0.27099 0.08889 +0.24187 0.08794 +0.21323 0.08610 +0.18509 0.08329 +0.15723 0.07937 +0.12983 0.07427 +0.10341 0.06792 +0.07823 0.06010 +0.05513 0.05071 +0.03565 0.04020 +0.02083 0.02951 +0.01107 0.02016 +0.00529 0.01298 +0.00211 0.00777 +0.00051 0.00355 +0.00000 0.00000 +0.00086 -0.00324 +0.00370 -0.00606 +0.00839 -0.00842 +0.01536 -0.01043 +0.02725 -0.01221 +0.04810 -0.01375 +0.07493 -0.01459 +0.10481 -0.01477 +0.13529 -0.01467 +0.16590 -0.01434 +0.19670 -0.01388 +0.22763 -0.01335 +0.25856 -0.01281 +0.28945 -0.01231 +0.32031 -0.01185 +0.35118 -0.01143 +0.38207 -0.01103 +0.41298 -0.01066 +0.44388 -0.01030 +0.47477 -0.00995 +0.50569 -0.00962 +0.53657 -0.00930 +0.56752 -0.00898 +0.59847 -0.00863 +0.62938 -0.00826 +0.66030 -0.00785 +0.69126 -0.00743 +0.72209 -0.00699 +0.75240 -0.00647 +0.78020 -0.00577 +0.80939 -0.00592 +0.83866 -0.00564 +0.86847 -0.00500 +0.89878 -0.00413 +0.92923 -0.00313 +0.95886 -0.00200 +0.98673 -0.00075 +1.00000 0.00000 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/fad23.dat b/aerosandbox/geometry/airfoil/airfoil_database/fad23.dat new file mode 100644 index 00000000..56b78aec --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/fad23.dat @@ -0,0 +1,80 @@ +FAD23 (c)Franck.Aguerre Profil polyvalent et gratteur +1.00000 0.00033 +0.98975 0.00055 +0.96564 0.00166 +0.93398 0.00391 +0.89822 0.00705 +0.86148 0.01056 +0.82574 0.01435 +0.79063 0.01863 +0.75511 0.02356 +0.71806 0.02906 +0.68036 0.03468 +0.64292 0.04016 +0.60541 0.04552 +0.56822 0.05070 +0.53137 0.05559 +0.49491 0.06014 +0.45889 0.06424 +0.42305 0.06787 +0.38762 0.07094 +0.35252 0.07340 +0.31763 0.07522 +0.28329 0.07632 +0.25003 0.07658 +0.21800 0.07584 +0.18706 0.07397 +0.15707 0.07090 +0.12830 0.06662 +0.10151 0.06118 +0.07741 0.05472 +0.05689 0.04762 +0.04085 0.04053 +0.02896 0.03391 +0.02047 0.02809 +0.01441 0.02306 +0.01002 0.01877 +0.00677 0.01509 +0.00435 0.01186 +0.00258 0.00896 +0.00134 0.00628 +0.00068 0.00376 +0.00038 0.00141 +0.00030 -0.00078 +0.00075 -0.00291 +0.00200 -0.00487 +0.00393 -0.00657 +0.00636 -0.00818 +0.00939 -0.00965 +0.01321 -0.01104 +0.01813 -0.01243 +0.02484 -0.01384 +0.03491 -0.01547 +0.05097 -0.01741 +0.07575 -0.01936 +0.10838 -0.02099 +0.14352 -0.02214 +0.17985 -0.02283 +0.21698 -0.02322 +0.25445 -0.02337 +0.29235 -0.02337 +0.33044 -0.02327 +0.36870 -0.02310 +0.40695 -0.02289 +0.44534 -0.02264 +0.48371 -0.02237 +0.52203 -0.02207 +0.56023 -0.02178 +0.59831 -0.02142 +0.63624 -0.02098 +0.67423 -0.02041 +0.71238 -0.01978 +0.74939 -0.01903 +0.78498 -0.01788 +0.81978 -0.01613 +0.85513 -0.01368 +0.89160 -0.01068 +0.92845 -0.00737 +0.96256 -0.00406 +0.98949 -0.00125 +1.00000 -0.00010 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/fad24.dat b/aerosandbox/geometry/airfoil/airfoil_database/fad24.dat new file mode 100644 index 00000000..3af31f15 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/fad24.dat @@ -0,0 +1,80 @@ +FAD24 (c)Franck.Aguerre Le meilleur des NACA2412 et ClarkY réunis, pour avion et planeur polyvalent +1.00000 0.00093 +0.98838 0.00340 +0.96230 0.00887 +0.92691 0.01601 +0.88789 0.02356 +0.84838 0.03087 +0.80884 0.03780 +0.76921 0.04436 +0.72955 0.05054 +0.68991 0.05632 +0.65040 0.06168 +0.61089 0.06660 +0.57146 0.07106 +0.53207 0.07505 +0.49287 0.07854 +0.45395 0.08148 +0.41550 0.08381 +0.37763 0.08543 +0.34038 0.08625 +0.30345 0.08624 +0.26738 0.08537 +0.23262 0.08353 +0.19932 0.08059 +0.16727 0.07646 +0.13672 0.07115 +0.10848 0.06480 +0.08353 0.05773 +0.06299 0.05055 +0.04725 0.04382 +0.03550 0.03780 +0.02678 0.03252 +0.02021 0.02784 +0.01515 0.02366 +0.01117 0.01991 +0.00800 0.01651 +0.00547 0.01339 +0.00350 0.01046 +0.00199 0.00770 +0.00092 0.00505 +0.00025 0.00252 +-0.00002 0.00012 +0.00011 -0.00224 +0.00069 -0.00466 +0.00179 -0.00706 +0.00339 -0.00943 +0.00549 -0.01172 +0.00810 -0.01397 +0.01131 -0.01612 +0.01522 -0.01819 +0.02001 -0.02016 +0.02602 -0.02210 +0.03378 -0.02412 +0.04417 -0.02629 +0.05867 -0.02856 +0.07954 -0.03078 +0.10808 -0.03276 +0.14205 -0.03409 +0.17899 -0.03462 +0.21769 -0.03450 +0.25759 -0.03388 +0.29838 -0.03292 +0.33970 -0.03173 +0.38131 -0.03038 +0.42292 -0.02893 +0.46435 -0.02733 +0.50567 -0.02559 +0.54697 -0.02376 +0.58860 -0.02185 +0.63062 -0.01987 +0.67253 -0.01786 +0.71434 -0.01580 +0.75609 -0.01371 +0.79798 -0.01158 +0.83999 -0.00942 +0.88196 -0.00724 +0.92332 -0.00506 +0.96087 -0.00307 +0.98809 -0.00159 +1.00000 -0.00094 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hg41.dat b/aerosandbox/geometry/airfoil/airfoil_database/hg41.dat new file mode 100644 index 00000000..9185f1f3 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hg41.dat @@ -0,0 +1,141 @@ +HG 41 (c)Slobodan Midic Hang glider 15% + 1.000000 0.000578 + 0.993556 0.000372 + 0.980538 0.000174 + 0.965685 0.000152 + 0.949523 0.000373 + 0.932599 0.000899 + 0.915293 0.001758 + 0.897794 0.002968 + 0.880195 0.004520 + 0.862542 0.006419 + 0.844823 0.008660 + 0.827043 0.011232 + 0.809178 0.014134 + 0.791201 0.017352 + 0.773093 0.020870 + 0.754830 0.024673 + 0.736387 0.028740 + 0.717734 0.033048 + 0.698861 0.037558 + 0.679787 0.042236 + 0.660507 0.047048 + 0.641083 0.051930 + 0.621684 0.056800 + 0.602450 0.061582 + 0.583417 0.066224 + 0.564595 0.070688 + 0.545965 0.074941 + 0.527508 0.078963 + 0.509214 0.082727 + 0.491061 0.086216 + 0.473040 0.089412 + 0.455134 0.092298 + 0.437329 0.094861 + 0.419618 0.097087 + 0.401982 0.098967 + 0.384416 0.100492 + 0.366900 0.101651 + 0.349420 0.102443 + 0.331956 0.102859 + 0.314484 0.102904 + 0.297000 0.102581 + 0.279504 0.101897 + 0.262033 0.100859 + 0.244627 0.099471 + 0.227346 0.097736 + 0.210245 0.095646 + 0.193386 0.093202 + 0.176821 0.090388 + 0.160604 0.087200 + 0.144781 0.083627 + 0.129418 0.079677 + 0.114598 0.075363 + 0.100443 0.070727 + 0.087105 0.065831 + 0.074759 0.060760 + 0.063536 0.055591 + 0.053513 0.050411 + 0.044696 0.045341 + 0.037055 0.040537 + 0.030510 0.036148 + 0.024968 0.032195 + 0.020302 0.028581 + 0.016351 0.025256 + 0.012988 0.022177 + 0.010140 0.019275 + 0.007737 0.016507 + 0.005694 0.013871 + 0.003958 0.011359 + 0.002524 0.008938 + 0.001411 0.006575 + 0.000623 0.004263 + 0.000148 0.002010 + -0.000029 -0.000167 + 0.000085 -0.002319 + 0.000514 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a/aerosandbox/geometry/airfoil/airfoil_database/hn1032.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn1032.dat new file mode 100644 index 00000000..d5e67cb5 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn1032.dat @@ -0,0 +1,102 @@ +HN 1032 F3J/Allround © Norbert Habbe +1.00000 0.00000 +0.99901 0.00015 +0.99606 0.00065 +0.99114 0.00152 +0.98429 0.00280 +0.97553 0.00443 +0.96489 0.00634 +0.95241 0.00848 +0.93815 0.01078 +0.92216 0.01325 +0.90451 0.01589 +0.88526 0.01869 +0.86448 0.02161 +0.84227 0.02462 +0.81871 0.02769 +0.79389 0.03077 +0.76791 0.03384 +0.74088 0.03688 +0.71289 0.03982 +0.68406 0.04267 +0.65451 0.04537 +0.62435 0.04791 +0.59369 0.05025 +0.56267 0.05238 +0.53140 0.05428 +0.50000 0.05591 +0.46861 0.05725 +0.43733 0.05828 +0.40631 0.05900 +0.37566 0.05937 +0.34549 0.05941 +0.31594 0.05909 +0.28711 0.05842 +0.25912 0.05737 +0.23209 0.05596 +0.20611 0.05420 +0.18129 0.05208 +0.15773 0.04961 +0.13552 0.04682 +0.11474 0.04370 +0.09549 0.04029 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a/aerosandbox/geometry/airfoil/airfoil_database/hn163tb.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn163tb.dat new file mode 100644 index 00000000..7483899e --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn163tb.dat @@ -0,0 +1,114 @@ +HN-163TB F3B © Norbert Habbe +1.00000 0.00000 +0.99901 0.00014 +0.99606 0.00062 +0.99114 0.00146 +0.98429 0.00268 +0.97553 0.00425 +0.96489 0.00610 +0.95241 0.00817 +0.93815 0.01040 +0.92216 0.01279 +0.90451 0.01534 +0.88526 0.01805 +0.86448 0.02088 +0.84227 0.02380 +0.81871 0.02679 +0.79389 0.02980 +0.76791 0.03281 +0.74088 0.03579 +0.71289 0.03871 +0.68406 0.04155 +0.65451 0.04427 +0.62435 0.04686 +0.59369 0.04927 +0.56267 0.05149 +0.53140 0.05350 +0.50000 0.05525 +0.46861 0.05674 +0.43733 0.05794 +0.40631 0.05882 +0.37566 0.05937 +0.34549 0.05958 +0.31594 0.05943 +0.28711 0.05891 +0.25912 0.05801 +0.23209 0.05672 +0.20611 0.05506 +0.18129 0.05302 +0.15773 0.05061 +0.13552 0.04785 +0.11474 0.04473 +0.09549 0.04130 +0.07784 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+0.99606 0.00024 +0.99901 0.00007 +1.00000 0.00000 +Profilbeiwerte +Profildicke(d): 8.35 % +Dickenrücklage(xd): 30.62 % +Profilwölbung(f): 1.85 % +Wölbungsrücklage(xf): 43.73 % +Momentenbeiwert(cm0): -0.0698 +Nullauftrieb(a0): -2.6332 ° +Stoßfreier Eintritt: 0.3062 ° +Ca bei stoßfreiem Eintritt: 0.3223 +Auftriebsanstieg: 6.6994 +Neutralpunktlage: 25.61 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn184.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn184.dat new file mode 100644 index 00000000..6b03573f --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn184.dat @@ -0,0 +1,114 @@ +HN-184 F3B © Norbert Habbe +1.00000 0.00000 +0.99901 0.00014 +0.99606 0.00059 +0.99114 0.00140 +0.98429 0.00257 +0.97553 0.00408 +0.96489 0.00587 +0.95241 0.00788 +0.93815 0.01006 +0.92216 0.01242 +0.90451 0.01495 +0.88526 0.01765 +0.86448 0.02048 +0.84227 0.02342 +0.81871 0.02643 +0.79389 0.02948 +0.76791 0.03254 +0.74088 0.03558 +0.71289 0.03857 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b/aerosandbox/geometry/airfoil/airfoil_database/hn184m.dat @@ -0,0 +1,114 @@ +HN-184M Planeur © Norbert Habbe +1.00000 0.00000 +0.99901 0.00017 +0.99606 0.00073 +0.99114 0.00170 +0.98429 0.00311 +0.97553 0.00491 +0.96489 0.00702 +0.95241 0.00937 +0.93815 0.01190 +0.92216 0.01461 +0.90451 0.01751 +0.88526 0.02057 +0.86448 0.02376 +0.84227 0.02704 +0.81871 0.03038 +0.79389 0.03375 +0.76791 0.03710 +0.74088 0.04041 +0.71289 0.04364 +0.68406 0.04675 +0.65451 0.04971 +0.62435 0.05251 +0.59369 0.05510 +0.56267 0.05746 +0.53140 0.05956 +0.50000 0.06137 +0.46861 0.06287 +0.43733 0.06403 +0.40631 0.06484 +0.37566 0.06528 +0.34549 0.06534 +0.31594 0.06500 +0.28711 0.06426 +0.25912 0.06310 +0.23209 0.06154 +0.20611 0.05957 +0.18129 0.05720 +0.15773 0.05444 +0.13552 0.05132 +0.11474 0.04784 +0.09549 0.04403 +0.07784 0.03994 +0.06185 0.03560 +0.04759 0.03105 +0.03511 0.02633 +0.02447 0.02149 +0.01571 0.01664 +0.00886 0.01190 +0.00394 0.00739 +0.00099 0.00328 +0.00000 0.00000 +0.00099 -0.00254 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+Momentenbeiwert(cm0): -0.0885 +Nullauftrieb(a0): -3.3195 ° +Stoßfreier Eintritt: 0.3489 ° +Ca bei stoßfreiem Eintritt: 0.4023 +Auftriebsanstieg: 6.707 +Neutralpunktlage: 25.63 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn188.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn188.dat new file mode 100644 index 00000000..e58a9d17 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn188.dat @@ -0,0 +1,114 @@ +HN-188 Planeur>3.5m © Norbert Habbe +1.00000 0.00000 +0.99901 0.00018 +0.99606 0.00077 +0.99114 0.00181 +0.98429 0.00332 +0.97553 0.00526 +0.96489 0.00755 +0.95241 0.01012 +0.93815 0.01289 +0.92216 0.01588 +0.90451 0.01908 +0.88526 0.02249 +0.86448 0.02606 +0.84227 0.02975 +0.81871 0.03353 +0.79389 0.03735 +0.76791 0.04117 +0.74088 0.04496 +0.71289 0.04868 +0.68406 0.05228 +0.65451 0.05572 +0.62435 0.05899 +0.59369 0.06203 +0.56267 0.06480 +0.53140 0.06728 +0.50000 0.06944 +0.46861 0.07124 +0.43733 0.07265 +0.40631 0.07367 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a/aerosandbox/geometry/airfoil/airfoil_database/hn211.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn211.dat new file mode 100644 index 00000000..b8c986e0 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn211.dat @@ -0,0 +1,114 @@ +HN-211 F3F-F3B © Norbert Habbe +1.00000 0.00000 +0.99901 0.00013 +0.99606 0.00056 +0.99114 0.00133 +0.98429 0.00244 +0.97553 0.00389 +0.96489 0.00560 +0.95241 0.00751 +0.93815 0.00957 +0.92216 0.01181 +0.90451 0.01421 +0.88526 0.01676 +0.86448 0.01944 +0.84227 0.02222 +0.81871 0.02506 +0.79389 0.02794 +0.76791 0.03083 +0.74088 0.03369 +0.71289 0.03651 +0.68406 0.03924 +0.65451 0.04186 +0.62435 0.04435 +0.59369 0.04667 +0.56267 0.04879 +0.53140 0.05070 +0.50000 0.05236 +0.46861 0.05376 +0.43733 0.05487 +0.40631 0.05569 +0.37566 0.05619 +0.34549 0.05637 +0.31594 0.05620 +0.28711 0.05569 +0.25912 0.05482 +0.23209 0.05360 +0.20611 0.05202 +0.18129 0.05009 +0.15773 0.04781 +0.13552 0.04520 +0.11474 0.04227 +0.09549 0.03904 +0.07784 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+Momentenbeiwert(cm0): -0.0666 +Nullauftrieb(a0): -2.5042 ° +Stoßfreier Eintritt: 0.274 ° +Ca bei stoßfreiem Eintritt: 0.3046 +Auftriebsanstieg: 6.6942 +Neutralpunktlage: 25.61 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn217.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn217.dat new file mode 100644 index 00000000..29e0faf0 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn217.dat @@ -0,0 +1,115 @@ +HN-217 F3J ©Norbert Habe +1.00000 0.00000 +0.99901 0.00017 +0.99606 0.00072 +0.99114 0.00168 +0.98429 0.00306 +0.97553 0.00483 +0.96489 0.00691 +0.95241 0.00921 +0.93815 0.01168 +0.92216 0.01432 +0.90451 0.01713 +0.88526 0.02010 +0.86448 0.02318 +0.84227 0.02634 +0.81871 0.02956 +0.79389 0.03278 +0.76791 0.03598 +0.74088 0.03913 +0.71289 0.04219 +0.68406 0.04514 +0.65451 0.04794 +0.62435 0.05058 +0.59369 0.05302 +0.56267 0.05525 +0.53140 0.05725 +0.50000 0.05900 +0.46861 0.06044 +0.43733 0.06157 +0.40631 0.06236 +0.37566 0.06280 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-3.2471 ° +Stoßfreier Eintritt: 0.3637 ° +Ca bei stoßfreiem Eintritt: 0.3959 +Auftriebsanstieg: 6.7249 +Neutralpunktlage: 25.68 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn239.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn239.dat new file mode 100644 index 00000000..4d61e8af --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn239.dat @@ -0,0 +1,114 @@ +HN-239 F3J © Norbert Habbe +1.00000 0.00000 +0.99901 0.00016 +0.99606 0.00067 +0.99114 0.00156 +0.98429 0.00285 +0.97553 0.00450 +0.96489 0.00645 +0.95241 0.00862 +0.93815 0.01095 +0.92216 0.01346 +0.90451 0.01614 +0.88526 0.01897 +0.86448 0.02193 +0.84227 0.02499 +0.81871 0.02810 +0.79389 0.03123 +0.76791 0.03436 +0.74088 0.03745 +0.71289 0.04047 +0.68406 0.04338 +0.65451 0.04617 +0.62435 0.04880 +0.59369 0.05123 +0.56267 0.05345 +0.53140 0.05543 +0.50000 0.05714 +0.46861 0.05856 +0.43733 0.05966 +0.40631 0.06044 +0.37566 0.06087 +0.34549 0.06095 +0.31594 0.06065 +0.28711 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b/aerosandbox/geometry/airfoil/airfoil_database/hn275s.dat new file mode 100644 index 00000000..0a571688 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn275s.dat @@ -0,0 +1,114 @@ +HN-275S Aile volante © Norbert Habbe +1.00000 0.00000 +0.99901 0.00004 +0.99606 0.00020 +0.99114 0.00053 +0.98429 0.00106 +0.97553 0.00180 +0.96489 0.00272 +0.95241 0.00377 +0.93815 0.00493 +0.92216 0.00621 +0.90451 0.00765 +0.88526 0.00924 +0.86448 0.01100 +0.84227 0.01292 +0.81871 0.01499 +0.79389 0.01720 +0.76791 0.01953 +0.74088 0.02197 +0.71289 0.02449 +0.68406 0.02708 +0.65451 0.02970 +0.62435 0.03232 +0.59369 0.03491 +0.56267 0.03743 +0.53140 0.03984 +0.50000 0.04210 +0.46861 0.04419 +0.43733 0.04608 +0.40631 0.04773 +0.37566 0.04912 +0.34549 0.05020 +0.31594 0.05095 +0.28711 0.05134 +0.25912 0.05136 +0.23209 0.05097 +0.20611 0.05016 +0.18129 0.04894 +0.15773 0.04727 +0.13552 0.04517 +0.11474 0.04265 +0.09549 0.03972 +0.07784 0.03644 +0.06185 0.03284 +0.04759 0.02896 +0.03511 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0.00000 +Profilbeiwerte +Profildicke(d): 10.28 % +Dickenrücklage(xd): 27.3 % +Profilwölbung(f): 0 % +Wölbungsrücklage(xf): 0 % +Momentenbeiwert(cm0): 0 +Nullauftrieb(a0): 0 ° +Stoßfreier Eintritt: 0 ° +Ca bei stoßfreiem Eintritt: 0 +Auftriebsanstieg: 6.7777 +Neutralpunktlage: 25.55 % +Profiltyp: Tropfen diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn276sa.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn276sa.dat new file mode 100644 index 00000000..deaf2f60 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn276sa.dat @@ -0,0 +1,114 @@ +HN-276SA Aile volante © Norbert Habbe +1.00000 0.00000 +0.99901 0.00006 +0.99600 0.00026 +0.99114 0.00060 +0.98429 0.00116 +0.97553 0.00193 +0.96489 0.00291 +0.95241 0.00406 +0.93815 0.00539 +0.92216 0.00689 +0.90451 0.00856 +0.88526 0.01041 +0.86448 0.01241 +0.84227 0.01453 +0.81871 0.01677 +0.79389 0.01908 +0.76791 0.02145 +0.74088 0.02386 +0.71289 0.02628 +0.68406 0.02868 +0.65451 0.03103 +0.62435 0.03332 +0.59369 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Norbert Habbe +1.00000 0.00000 +0.99901 0.00018 +0.99606 0.00078 +0.99114 0.00183 +0.98429 0.00337 +0.97553 0.00535 +0.96489 0.00769 +0.95241 0.01031 +0.93815 0.01314 +0.92216 0.01620 +0.90451 0.01949 +0.88526 0.02298 +0.86448 0.02665 +0.84227 0.03045 +0.81871 0.03433 +0.79389 0.03827 +0.76791 0.04221 +0.74088 0.04613 +0.71289 0.04997 +0.68406 0.05370 +0.65451 0.05727 +0.62435 0.06066 +0.59369 0.06381 +0.56267 0.06669 +0.53140 0.06927 +0.50000 0.07151 +0.46861 0.07339 +0.43733 0.07487 +0.40631 0.07594 +0.37566 0.07658 +0.34549 0.07677 +0.31594 0.07649 +0.28711 0.07575 +0.25912 0.07451 +0.23209 0.07279 +0.20611 0.07058 +0.18129 0.06790 +0.15773 0.06475 +0.13552 0.06115 +0.11474 0.05713 +0.09549 0.05270 +0.07784 0.04791 +0.06185 0.04281 +0.04759 0.03743 +0.03511 0.03183 +0.02447 0.02606 +0.01571 0.02026 +0.00886 0.01456 +0.00394 0.00910 +0.00097 0.00410 +0.00000 0.00000 +0.00099 -0.00332 +0.00377 -0.00689 +0.00886 -0.01052 +0.01571 -0.01388 +0.02447 -0.01710 +0.03511 -0.02010 +0.04759 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stoßfreiem Eintritt: 0.4023 +Auftriebsanstieg: 6.821 +Neutralpunktlage: 25.8 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn304ta.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn304ta.dat new file mode 100644 index 00000000..d7b7c1f3 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn304ta.dat @@ -0,0 +1,114 @@ +HN-304TA Planeur>3.5m © Norbert Habbe +1.00000 0.00000 +0.99901 0.00018 +0.99606 0.00079 +0.99114 0.00186 +0.98429 0.00342 +0.97553 0.00542 +0.96489 0.00780 +0.95241 0.01046 +0.93815 0.01334 +0.92216 0.01645 +0.90451 0.01979 +0.88526 0.02334 +0.86448 0.02707 +0.84227 0.03093 +0.81871 0.03488 +0.79389 0.03888 +0.76791 0.04289 +0.74088 0.04687 +0.71289 0.05078 +0.68406 0.05456 +0.65451 0.05820 +0.62435 0.06165 +0.59369 0.06485 +0.56267 0.06779 +0.53140 0.07041 +0.50000 0.07269 +0.46861 0.07460 +0.43733 0.07611 +0.40631 0.07720 +0.37566 0.07785 +0.34549 0.07806 +0.31594 0.07777 +0.28711 0.07702 +0.25912 0.07576 +0.23209 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Eintritt: 0.3516 +Auftriebsanstieg: 6.821 +Neutralpunktlage: 25.8 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn30s.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn30s.dat new file mode 100644 index 00000000..a51ede44 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn30s.dat @@ -0,0 +1,102 @@ + HN-30s Aile volante © Norbert Habbe +1.00000 0.00000 +0.99901 0.00003 +0.99606 0.00017 +0.99114 0.00043 +0.98429 0.00085 +0.97553 0.00144 +0.96489 0.00221 +0.95241 0.00313 +0.93815 0.00420 +0.92216 0.00542 +0.90451 0.00681 +0.88526 0.00836 +0.86448 0.01005 +0.84227 0.01187 +0.81871 0.01381 +0.79389 0.01583 +0.76791 0.01793 +0.74088 0.02008 +0.71289 0.02225 +0.68406 0.02442 +0.65451 0.02656 +0.62435 0.02865 +0.59369 0.03064 +0.56267 0.03249 +0.53140 0.03420 +0.50000 0.03572 +0.46861 0.03706 +0.43733 0.03822 +0.40631 0.03916 +0.37566 0.03990 +0.34549 0.04041 +0.31594 0.04069 +0.28711 0.04072 +0.25912 0.04049 +0.23209 0.04000 +0.20611 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b/aerosandbox/geometry/airfoil/airfoil_database/hn315s.dat new file mode 100644 index 00000000..29b8fffc --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn315s.dat @@ -0,0 +1,74 @@ +HN-315S Aile volante © Norbert Habbe +1.00000 0.00000 +0.99646 0.00021 +0.98625 0.00104 +0.97017 0.00261 +0.94885 0.00468 +0.92247 0.00693 +0.89118 0.00940 +0.85538 0.01212 +0.81560 0.01509 +0.77237 0.01826 +0.72627 0.02153 +0.67789 0.02480 +0.62777 0.02796 +0.57647 0.03092 +0.52456 0.03359 +0.47261 0.03588 +0.42116 0.03773 +0.35788 0.03906 +0.30237 0.03982 +0.25250 0.03996 +0.20796 0.03941 +0.16841 0.03816 +0.13352 0.03618 +0.10303 0.03348 +0.07630 0.03008 +0.05373 0.02600 +0.03499 0.02133 +0.02016 0.01614 +0.00926 0.01064 +0.00240 0.00510 +0.00000 0.00000 +0.00240 -0.00510 +0.00926 -0.01064 +0.02016 -0.01614 +0.03499 -0.02133 +0.05373 -0.02600 +0.07630 -0.03008 +0.10303 -0.03348 +0.13352 -0.03618 +0.16841 -0.03816 +0.20796 -0.03941 +0.25250 -0.03996 +0.30237 -0.03982 +0.35788 -0.03906 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0.2608 ° +Ca bei stoßfreiem Eintritt: 0.2708 +Auftriebsanstieg: 6.6716 +Neutralpunktlage: 25.59 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn326.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn326.dat new file mode 100644 index 00000000..57001aa6 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn326.dat @@ -0,0 +1,114 @@ +HN-326 F3F © Norbert Habbe +1.000000 0.000000 +0.999013 0.000119 +0.996057 0.000494 +0.991144 0.001160 +0.984292 0.002141 +0.975528 0.003423 +0.964888 0.004943 +0.952414 0.006647 +0.938153 0.008497 +0.922164 0.010490 +0.904508 0.012626 +0.885257 0.014906 +0.864484 0.017314 +0.842274 0.019823 +0.818712 0.022410 +0.793893 0.025061 +0.767913 0.027741 +0.740877 0.030436 +0.712890 0.033117 +0.684062 0.035758 +0.654508 0.038327 +0.624345 0.040806 +0.593691 0.043155 +0.562667 0.045360 +0.531395 0.047378 +0.500000 0.049197 +0.468605 0.050790 +0.437333 0.052136 +0.406309 0.053219 +0.375655 0.054003 +0.345492 0.054485 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+Dickenrücklage(xd): 27,30 % +Profilwölbung(f): 1,85 % +Wölbungsrücklage(xf): 43,73 % +Momentenbeiwert(cm0): -0,0642 +Nullauftrieb(a 0): -2,4631 ° +Stoßfreier Eintritt: 0,3804 ° +Ca bei stoßfreiem Eintritt: 0,3118 +Auftriebsanstieg: 6,6774 +Neutralpunktlage: 25,35 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn333.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn333.dat new file mode 100644 index 00000000..ef5b6c59 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn333.dat @@ -0,0 +1,114 @@ +HN-333 F3J © Norbert Habbe +1.000000 0.000000 +0.999013 0.000150 +0.996057 0.000640 +0.991144 0.001509 +0.984292 0.002763 +0.975528 0.004375 +0.964888 0.006281 +0.952414 0.008410 +0.938153 0.010708 +0.922164 0.013183 +0.904508 0.015835 +0.885257 0.018652 +0.864484 0.021599 +0.842274 0.024641 +0.818712 0.027755 +0.793893 0.030901 +0.767913 0.034044 +0.740877 0.037159 +0.712890 0.040210 +0.684062 0.043163 +0.654508 0.045991 +0.624345 0.048667 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a/aerosandbox/geometry/airfoil/airfoil_database/hn354.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn354.dat new file mode 100644 index 00000000..95a3e1e2 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn354.dat @@ -0,0 +1,114 @@ +HN-354 F3B © Norbert Habbe +1.00000 0.00000 +0.99895 0.00014 +0.99586 0.00065 +0.99097 0.00148 +0.98417 0.00270 +0.97553 0.00423 +0.96483 0.00606 +0.95241 0.00810 +0.93815 0.01030 +0.92216 0.01266 +0.90451 0.01519 +0.88526 0.01787 +0.86448 0.02067 +0.84227 0.02355 +0.81871 0.02649 +0.79389 0.02945 +0.76791 0.03241 +0.74088 0.03532 +0.71289 0.03818 +0.68406 0.04093 +0.65451 0.04357 +0.62435 0.04606 +0.59369 0.04837 +0.56267 0.05049 +0.53140 0.05239 +0.50000 0.05405 +0.46861 0.05543 +0.43733 0.05652 +0.40631 0.05731 +0.37566 0.05777 +0.34549 0.05790 +0.31594 0.05767 +0.28711 0.05710 +0.25912 0.05615 +0.23209 0.05483 +0.20611 0.05316 +0.18129 0.05112 +0.15773 0.04874 +0.13552 0.04602 +0.11474 0.04297 +0.09549 0.03962 +0.07784 0.03600 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+Stoßfreier Eintritt: 0.2958 ° +Ca bei stoßfreiem Eintritt: 0.3305 +Auftriebsanstieg: 6.6843 +Neutralpunktlage: 25.6 % +Profiltyp: Profil diff --git a/aerosandbox/geometry/airfoil/airfoil_database/hn354es.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn354es.dat new file mode 100644 index 00000000..11804632 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn354es.dat @@ -0,0 +1,102 @@ +HN-354ES F3F © Norbert Habbe +1.000000 0.000000 +0.999013 0.000122 +0.996057 0.000538 +0.991144 0.001268 +0.984292 0.002346 +0.975528 0.003735 +0.964888 0.005363 +0.952414 0.007214 +0.938153 0.009210 +0.922164 0.011374 +0.904508 0.013702 +0.885257 0.016179 +0.864484 0.018784 +0.842274 0.021486 +0.818712 0.024259 +0.793893 0.027069 +0.767913 0.029889 +0.740877 0.032689 +0.712890 0.035445 +0.684062 0.038118 +0.654508 0.040690 +0.624345 0.043137 +0.593691 0.045413 +0.562667 0.047507 +0.531395 0.049387 +0.500000 0.051033 +0.468605 0.052417 +0.437333 0.053530 +0.406309 0.054350 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a/aerosandbox/geometry/airfoil/airfoil_database/hn450s.dat b/aerosandbox/geometry/airfoil/airfoil_database/hn450s.dat new file mode 100644 index 00000000..bf3c4c2d --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/hn450s.dat @@ -0,0 +1,114 @@ +HN-450S Planeur © Norbert Habbe +1.00000 0.00000 +0.99901 0.00012 +0.99606 0.00050 +0.99114 0.00119 +0.98429 0.00220 +0.97553 0.00354 +0.96489 0.00516 +0.95241 0.00704 +0.93815 0.00913 +0.92216 0.01144 +0.90451 0.01397 +0.88526 0.01670 +0.86448 0.01959 +0.84227 0.02261 +0.81871 0.02574 +0.79389 0.02893 +0.76791 0.03213 +0.74088 0.03530 +0.71289 0.03841 +0.68406 0.04141 +0.65451 0.04428 +0.62435 0.04701 +0.59369 0.04955 +0.56267 0.05190 +0.53140 0.05403 +0.50000 0.05591 +0.46861 0.05752 +0.43733 0.05881 +0.40631 0.05978 +0.37566 0.06041 +0.34549 0.06068 +0.31594 0.06058 +0.28711 0.06008 +0.25912 0.05919 +0.23209 0.05790 +0.20611 0.05622 +0.18129 0.05415 +0.15773 0.05168 +0.13552 0.04885 +0.11474 0.04565 +0.09549 0.04212 +0.07784 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en F3B (en particulier par +l'équipe Genvrin Legou sur les Autans) et il a aussi été utilisé en durée +vitesse avec un certain succès il y a quelques années par le club des 5A. +J'ai moi même un ancien F3B de 1991 classe inter équipé de ce profil et j'en +suis fort satisfait. 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+0.88811189 0.00537593 +0.85210000 0.00715433 +0.81090000 0.00947233 +0.76610000 0.01213000 +0.71850000 0.01526000 +0.66433566 0.01923821 +0.60839161 0.02355909 +0.56510000 0.02719108 +0.51270000 0.03150000 +0.49650350 0.03282718 +0.46070000 0.03561776 +0.44055944 0.03710046 +0.40970000 0.03920677 +0.38461538 0.04079384 +0.35664336 0.04247156 +0.31260000 0.04417553 +0.26740000 0.04499048 +0.22480000 0.04473347 +0.18881119 0.04376000 +0.16083916 0.04220000 +0.14910000 0.04126979 +0.13286713 0.03983442 +0.11640000 0.03805455 +0.10489510 0.03655268 +0.09090909 0.03447692 +0.08730000 0.03390579 +0.07692308 0.03201979 +0.06190000 0.02897265 +0.04895105 0.02568109 +0.04060000 0.02333065 +0.03496503 0.02151273 +0.02797203 0.01910357 +0.02360000 0.01736291 +0.02097902 0.01614595 +0.01398601 0.01280523 +0.01090000 0.01108274 +0.00699301 0.00839491 +0.00280000 0.00432986 +0.00000000 0.00000000 +0.00280000 -0.00432986 +0.00699301 -0.00839491 +0.01090000 -0.01108274 +0.01398601 -0.01280523 +0.02097902 -0.01614595 +0.02360000 -0.01736291 +0.02797203 -0.01910357 +0.03496503 -0.02151273 +0.04060000 -0.02333065 +0.04895105 -0.02568109 +0.06190000 -0.02897265 +0.07692308 -0.03201979 +0.08730000 -0.03390579 +0.09090909 -0.03447692 +0.10489510 -0.03655268 +0.11640000 -0.03805455 +0.13286713 -0.03983442 +0.14910000 -0.04126979 +0.16083916 -0.04220000 +0.18881119 -0.04376000 +0.22480000 -0.04473347 +0.26740000 -0.04499048 +0.31260000 -0.04417553 +0.35664336 -0.04247156 +0.38461538 -0.04079384 +0.40970000 -0.03920677 +0.44055944 -0.03710046 +0.46070000 -0.03561776 +0.49650350 -0.03282718 +0.51270000 -0.03150000 +0.56510000 -0.02719108 +0.60839161 -0.02355909 +0.66433566 -0.01923821 +0.71850000 -0.01526000 +0.76610000 -0.01213000 +0.81090000 -0.00947233 +0.85210000 -0.00715433 +0.88811189 -0.00537593 +0.92140000 -0.00373713 +0.94405594 -0.00261001 +0.97020000 -0.00140283 +1.00000000 0.00000000 + +le calage de l'aile pour un MG05 ? + +Il te faut le caler a zero, tout comme le stab, et c'est le debattement +des volets (30% corde) qui donnera le calage en vol normal. exemple pour +une corde de 25 cm et un debattement de 6 mm des volets vers le bas ca +nous fait un calage equivalent de 1.5°. et 6mm vers le haut tu voles +pareil sur le dos... Ensuite tu baisses les volet a 15 mm ca te fait un +profil hyper creux et un calage compatible pour la gratte de 3.4°, il +faut meme un peu compenser par un mixage profondeur a piquer... + +> le MG05 supportera t'il le +> saumon de 135mmm? + +pas de pb le voltij fait 110mm au saumons de il ne declenche pas en +virage lent. + + +-- +Marcel Guwang + +Toulouse, FRANCE diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mg05na09_210.dat b/aerosandbox/geometry/airfoil/airfoil_database/mg05na09_210.dat new file mode 100644 index 00000000..0b78f9c4 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mg05na09_210.dat @@ -0,0 +1,92 @@ +Mg05EtNaca09210 pour Profil du stabilisateur L213 (ph.jambon.free.fr) +1.0000000 0.0004725 +0.9702000 0.0027132 +0.9440559 0.0046206 +0.9214000 0.0062803 +0.8881119 0.0086645 +0.8521000 0.0111810 +0.8109000 0.0141119 +0.7661000 0.0172801 +0.7185000 0.0206804 +0.6643357 0.0246203 +0.6083916 0.0286257 +0.5651000 0.0317393 +0.5127000 0.0352871 +0.4965035 0.0363446 +0.4607000 0.0385164 +0.4405594 0.0396542 +0.4097000 0.0412206 +0.3846154 0.0423557 +0.3566434 0.0434828 +0.3126000 0.0445643 +0.2674000 0.0449014 +0.2248000 0.0443129 +0.1888112 0.0431046 +0.1608392 0.0414966 +0.1491000 0.0406343 +0.1328671 0.0391972 +0.1164000 0.0375330 +0.1048951 0.0360724 +0.0909091 0.0341719 +0.0873000 0.0336420 +0.0769231 0.0318187 +0.0619000 0.0290207 +0.0489511 0.0258661 +0.0406000 0.0236353 +0.0349650 0.0220142 +0.0279720 0.0195910 +0.0236000 0.0171515 +0.0209790 0.0156023 +0.0139860 0.0114222 +0.0109000 0.0094534 +0.0069930 0.0067072 +0.0028000 0.0031699 +0.0000000 0.0000000 +0.0028000 -0.0031699 +0.0069930 -0.0067072 +0.0109000 -0.0094534 +0.0139860 -0.0114222 +0.0209790 -0.0156023 +0.0236000 -0.0171515 +0.0279720 -0.0195910 +0.0349650 -0.0220142 +0.0406000 -0.0236353 +0.0489511 -0.0258661 +0.0619000 -0.0290207 +0.0769231 -0.0318187 +0.0873000 -0.0336420 +0.0909091 -0.0341719 +0.1048951 -0.0360724 +0.1164000 -0.0375330 +0.1328671 -0.0391972 +0.1491000 -0.0406343 +0.1608392 -0.0414966 +0.1888112 -0.0431046 +0.2248000 -0.0443129 +0.2674000 -0.0449014 +0.3126000 -0.0445643 +0.3566434 -0.0434828 +0.3846154 -0.0423557 +0.4097000 -0.0412206 +0.4405594 -0.0396542 +0.4607000 -0.0385164 +0.4965035 -0.0363446 +0.5127000 -0.0352871 +0.5651000 -0.0317393 +0.6083916 -0.0286257 +0.6643357 -0.0246203 +0.7185000 -0.0206804 +0.7661000 -0.0172801 +0.8109000 -0.0141119 +0.8521000 -0.0111810 +0.8881119 -0.0086645 +0.9214000 -0.0062803 +0.9440559 -0.0046206 +0.9702000 -0.0027132 +1.0000000 -0.0004725 + +20 nov 2005 +Avec Thierry Platon nous avons trouvé par hasard que le mélange du NACA 009 +et du MG05 à 50% étais encore meilleur e CX les polaires sont sur mon site a +la page http://ph.jambon.free.fr/mes_modeles/l213_1div.htm + diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mg06.dat b/aerosandbox/geometry/airfoil/airfoil_database/mg06.dat new file mode 100644 index 00000000..b7ced67c --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mg06.dat @@ -0,0 +1,74 @@ +MG06 (c)Marcel Guwang volets a 30% +1 0 +0.9968 0.000100002 +0.98745 0.000503073 +0.9722 0.001401403 +0.9513 0.002807158 +0.9251 0.004723925 +0.8938 0.00716284 +0.8581 0.010236894 +0.8183 0.013959859 +0.7752 0.01824146 +0.7291 0.023073397 +0.6809 0.028318704 +0.6312 0.033720824 +0.5808 0.039066302 +0.5304 0.043883344 +0.4804 0.047775115 +0.4307 0.050961099 +0.3819 0.053405104 +0.33405 0.055124873 +0.2876 0.056018461 +0.24358 0.055940037 +0.2024 0.054836831 +0.16442 0.052680119 +0.12993 0.049453821 +0.09921 0.045164948 +0.07244 0.039882701 +0.04978 0.033699598 +0.0313 0.026763013 +0.01702 0.019318368 +0.0069 0.01162968 +0.0009 0.003103937 +0 0 +0.0005 -0.0017 +0.0059 -0.0055 +0.0165 -0.0093 +0.032 -0.0126 +0.0524 -0.0152 +0.0778 -0.0171 +0.1078 -0.0182 +0.1423 -0.0188 +0.1811 -0.01881 +0.2236 -0.0183 +0.2695 -0.0176 +0.3181 -0.0167 +0.3689 -0.0157 +0.4213 -0.0146 +0.4746 -0.0134 +0.5282 -0.0121 +0.5816 -0.0109 +0.634 -0.0096 +0.6849 -0.0084 +0.7337 -0.0073 +0.7798 -0.0062 +0.8227 -0.0052 +0.8619 -0.0043 +0.8963 -0.0034 +0.9272 -0.0026 +0.9526 -0.0019 +0.9728 -0.0011 +0.9876 -0.0004 +0.9968 -0.0001 +1 0 + +Mais je tiens a preciser que ce profil necessite des volets a 30% de +corde et que sans c'est pas la peine d'essayer +epaisseur relative 7.4% +courbure 2% +cmo -0.013 +cm stable de alpha = -1 a +9 (-0.0129 a -0.0137) + c'est ce qui donne la super stabilité en trajectoire du Miraj. +czmax 1.0 sans volet + 1.35 avec 10° de volet (c'est la que ca rebondi bien... gazzzz) +Marcel Guwang \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mg08.dat b/aerosandbox/geometry/airfoil/airfoil_database/mg08.dat new file mode 100644 index 00000000..b1650d04 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mg08.dat @@ -0,0 +1,65 @@ +MG 08 (c)Marcel Guwang volet a 30% +1.000000 0.000000 +0.996700 0.000700 +0.987100 0.001300 +0.971500 0.002400 +0.950400 0.004100 +0.924200 0.006300 +0.893600 0.009100 +0.859000 0.012600 +0.820900 0.016900 +0.779700 0.021700 +0.736000 0.027000 +0.690200 0.032600 +0.597000 0.043900 +0.572000 0.046700 +0.543700 0.049800 +0.495000 0.054500 +0.444000 0.058400 +0.396000 0.061100 +0.347300 0.062600 +0.301300 0.063200 +0.258000 0.062500 +0.215900 0.060300 +0.177400 0.057100 +0.142000 0.052900 +0.110200 0.047800 +0.082100 0.041800 +0.057900 0.035200 +0.037800 0.028000 +0.021900 0.020500 +0.010300 0.013000 +0.002900 0.005900 +0.000000 0.000000 +0.002800 -0.004600 +0.011700 -0.008900 +0.025800 -0.012900 +0.045000 -0.016400 +0.069100 -0.019200 +0.097800 -0.021500 +0.131100 -0.023000 +0.168500 -0.024000 +0.209700 -0.024300 +0.254300 -0.024100 +0.301900 -0.023500 +0.351800 -0.022500 +0.403700 -0.021300 +0.456700 -0.019400 +0.510500 -0.017500 +0.569000 -0.015400 +0.617500 -0.013600 +0.669500 -0.011800 +0.719700 -0.010000 +0.764000 -0.008400 +0.812200 -0.006700 +0.853300 -0.005200 +0.890200 -0.003900 +0.922500 -0.002800 +0.949600 -0.001800 +0.971300 -0.001000 +0.987000 -0.000500 +0.996700 -0.000100 +1.000000 0.000000 + +le MG08 qui est sur l'aile de +l'avantaj et de l'essoraj \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh126.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh126.dat new file mode 100644 index 00000000..c55b1ea7 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh126.dat @@ -0,0 +1,64 @@ +MH 126 for the root region of propellers (C) Martin Hepperle + 1.00000000 0.00000000 + 0.99636432 0.00115043 + 0.98628312 0.00470810 + 0.97110124 0.01017924 + 0.95119615 0.01645085 + 0.92622474 0.02308577 + 0.89624878 0.03029323 + 0.86177479 0.03813446 + 0.82332883 0.04651305 + 0.78148171 0.05530490 + 0.73682774 0.06433226 + 0.68997655 0.07339185 + 0.64153687 0.08224884 + 0.59210773 0.09065599 + 0.54226726 0.09835550 + 0.49256700 0.10509387 + 0.44352593 0.11062740 + 0.39562860 0.11472768 + 0.34932453 0.11719043 + 0.30503218 0.11778359 + 0.26297576 0.11626958 + 0.22324779 0.11265706 + 0.18605664 0.10711285 + 0.15165397 0.09980278 + 0.12028173 0.09092344 + 0.09217699 0.08068888 + 0.06754269 0.06932781 + 0.04653844 0.05710757 + 0.02929912 0.04434720 + 0.01594370 0.03141202 + 0.00657650 0.01872540 + 0.00129245 0.00683022 + 0.00036267 -0.00332302 + 0.00548172 -0.01169320 + 0.01712468 -0.01951081 + 0.03404728 -0.02720397 + 0.05582202 -0.03448066 + 0.08213090 -0.04117303 + 0.11261629 -0.04714194 + 0.14689962 -0.05222522 + 0.18461363 -0.05628736 + 0.22530932 -0.05923099 + 0.26847323 -0.06083759 + 0.31377541 -0.06079201 + 0.36104265 -0.05897322 + 0.41005220 -0.05538629 + 0.46066294 -0.05016217 + 0.51261278 -0.04371187 + 0.56540111 -0.03645930 + 0.61847166 -0.02878860 + 0.67120899 -0.02110720 + 0.72292795 -0.01382477 + 0.77286809 -0.00734130 + 0.82019146 -0.00201415 + 0.86398913 0.00187129 + 0.90329990 0.00415101 + 0.93714358 0.00478259 + 0.96444757 0.00393289 + 0.98423914 0.00223881 + 0.99607983 0.00064792 + 1.00000000 0.00000000 + +http://www.MH-AeroTools.de \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh16.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh16.dat new file mode 100644 index 00000000..8f0cae41 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh16.dat @@ -0,0 +1,132 @@ +MH 16 ©Martin Hepperle Designed for pylon racing +1.000000 0.000000 +0.959588 0.008495 +0.924641 0.016525 +0.893669 0.024029 +0.865405 0.030962 +0.838804 0.037295 +0.813045 0.043015 +0.787530 0.048126 +0.761885 0.052646 +0.735957 0.056609 +0.709812 0.060067 +0.683638 0.063074 +0.657607 0.065684 +0.631857 0.067939 +0.606496 0.069877 +0.581596 0.071527 +0.557197 0.072912 +0.533305 0.074048 +0.509893 0.074943 +0.486902 0.075598 +0.464255 0.076010 +0.441890 0.076178 +0.419762 0.076104 +0.397852 0.075792 +0.376154 0.075249 +0.354689 0.074487 +0.333493 0.073519 +0.312625 0.072359 +0.292163 0.071029 +0.272198 0.069547 +0.252813 0.067932 +0.234077 0.066200 +0.216044 0.064359 +0.198754 0.062419 +0.182234 0.060383 +0.166494 0.058252 +0.151534 0.056021 +0.137336 0.053685 +0.123872 0.051234 +0.111117 0.048664 +0.099050 0.045975 +0.087660 0.043174 +0.076942 0.040276 +0.066899 0.037298 +0.057539 0.034267 +0.048879 0.031215 +0.040943 0.028181 +0.033758 0.025206 +0.027348 0.022331 +0.021720 0.019588 +0.016867 0.017002 +0.012769 0.014589 +0.009392 0.012358 +0.006686 0.010310 +0.004589 0.008437 +0.003021 0.006725 +0.001895 0.005150 +0.001125 0.003688 +0.000647 0.002313 +0.000419 0.001001 +0.000419 -0.000273 +0.000647 -0.001531 +0.001125 -0.002796 +0.001895 -0.004090 +0.003021 -0.005434 +0.004589 -0.006848 +0.006686 -0.008349 +0.009392 -0.009949 +0.012769 -0.011654 +0.016867 -0.013461 +0.021720 -0.015365 +0.027348 -0.017351 +0.033758 -0.019401 +0.040943 -0.021489 +0.048879 -0.023583 +0.057539 -0.025650 +0.066899 -0.027660 +0.076942 -0.029589 +0.087660 -0.031416 +0.099050 -0.033128 +0.111117 -0.034714 +0.123872 -0.036171 +0.137336 -0.037499 +0.151534 -0.038704 +0.166494 -0.039795 +0.182234 -0.040780 +0.198754 -0.041666 +0.216044 -0.042458 +0.234077 -0.043158 +0.252813 -0.043770 +0.272198 -0.044292 +0.292163 -0.044724 +0.312625 -0.045061 +0.333493 -0.045299 +0.354689 -0.045433 +0.376154 -0.045459 +0.397852 -0.045371 +0.419762 -0.045166 +0.441890 -0.044838 +0.464255 -0.044385 +0.486902 -0.043802 +0.509893 -0.043086 +0.533305 -0.042232 +0.557197 -0.041239 +0.581596 -0.040105 +0.606496 -0.038831 +0.631857 -0.037417 +0.657607 -0.035867 +0.683638 -0.034183 +0.709812 -0.032372 +0.735957 -0.030438 +0.761885 -0.028389 +0.787530 -0.026210 +0.813045 -0.023860 +0.838804 -0.021267 +0.865405 -0.018328 +0.893669 -0.014910 +0.924641 -0.010850 +0.959588 -0.005954 +1.000000 0.000000 + +Designed for pylon racing model aircraft (Q500 class) +http://www.mh-aerotools.de/airfoils/mh16koo.htm +Characteristics +Thickness: 12.13% +Larger moment coefficient cm c/4 than e.g. MH 18, but similar to MH 27. +Well suited for the Quickie 500. +Can be used at Reynolds numbers of 300'000 and above. +Developed for lift coefficients between -0.1 and 0.6. +General remark: The potential for the reduction of the minimum drag is only very small, as the older airfoils were already close to the optimum. Improvements are mainly possible in the behavior and the width of the low drag bucket. +See also MH 17, MH 18, MH 18B, MH 20, MH 22, MH 27. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh17.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh17.dat new file mode 100644 index 00000000..0e62f49c --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh17.dat @@ -0,0 +1,152 @@ +MH 17 ©Martin Hepperle Designed for pylon racing +1.000000 0.000000 +0.993894 0.000399 +0.983357 0.001545 +0.970742 0.003043 +0.955903 0.004984 +0.939780 0.007312 +0.923695 0.009868 +0.907824 0.012621 +0.891857 0.015605 +0.875745 0.018806 +0.859514 0.022179 +0.843107 0.025685 +0.826607 0.029243 +0.810208 0.032748 +0.793932 0.036140 +0.777731 0.039391 +0.761569 0.042485 +0.745403 0.045414 +0.729200 0.048185 +0.712947 0.050804 +0.696649 0.053279 +0.680317 0.055611 +0.663954 0.057804 +0.647564 0.059861 +0.631154 0.061782 +0.614732 0.063566 +0.598300 0.065212 +0.581855 0.066718 +0.565405 0.068086 +0.548954 0.069309 +0.532499 0.070388 +0.516037 0.071321 +0.499569 0.072106 +0.483096 0.072745 +0.466608 0.073237 +0.450108 0.073587 +0.433598 0.073796 +0.417070 0.073866 +0.400531 0.073804 +0.383984 0.073610 +0.367422 0.073289 +0.350858 0.072844 +0.334296 0.072276 +0.317738 0.071586 +0.301194 0.070773 +0.284670 0.069834 +0.268176 0.068765 +0.251727 0.067560 +0.235331 0.066208 +0.218998 0.064700 +0.202752 0.063020 +0.186612 0.061151 +0.170597 0.059073 +0.154744 0.056760 +0.139075 0.054183 +0.123622 0.051310 +0.108410 0.048106 +0.093454 0.044534 +0.078795 0.040570 +0.064484 0.036188 +0.050660 0.031400 +0.037699 0.026319 +0.026460 0.021324 +0.017868 0.016976 +0.011873 0.013492 +0.007732 0.010691 +0.004802 0.008319 +0.002708 0.006188 +0.001260 0.004181 +0.000373 0.002249 +0.000013 0.000407 +0.000153 -0.001386 +0.000865 -0.003200 +0.002206 -0.004938 +0.004184 -0.006568 +0.006875 -0.008155 +0.010519 -0.009805 +0.015612 -0.011651 +0.022977 -0.013838 +0.033434 -0.016413 +0.046716 -0.019165 +0.061565 -0.021796 +0.077098 -0.024187 +0.092980 -0.026338 +0.109087 -0.028278 +0.125358 -0.030041 +0.141773 -0.031657 +0.158291 -0.033153 +0.174900 -0.034551 +0.191566 -0.035868 +0.208271 -0.037113 +0.225004 -0.038291 +0.241756 -0.039409 +0.258519 -0.040468 +0.275282 -0.041468 +0.292043 -0.042408 +0.308802 -0.043286 +0.325549 -0.044098 +0.342283 -0.044841 +0.359006 -0.045508 +0.375714 -0.046097 +0.392405 -0.046602 +0.409082 -0.047016 +0.425744 -0.047336 +0.442388 -0.047557 +0.459018 -0.047672 +0.475638 -0.047680 +0.492249 -0.047577 +0.508850 -0.047361 +0.525450 -0.047030 +0.542057 -0.046586 +0.558672 -0.046032 +0.575300 -0.045371 +0.591946 -0.044609 +0.608612 -0.043752 +0.625299 -0.042808 +0.642005 -0.041783 +0.658729 -0.040685 +0.675476 -0.039519 +0.692248 -0.038295 +0.709042 -0.037020 +0.725861 -0.035702 +0.742705 -0.034349 +0.759554 -0.032969 +0.776381 -0.031563 +0.793156 -0.030122 +0.809846 -0.028632 +0.826427 -0.027068 +0.842887 -0.025400 +0.859227 -0.023598 +0.875481 -0.021635 +0.891676 -0.019489 +0.907758 -0.017160 +0.923760 -0.014644 +0.939979 -0.011896 +0.956211 -0.008961 +0.971059 -0.006130 +0.983588 -0.003636 +0.993993 -0.001491 +1.000000 0.000000 + +Designed for pylon racing model aircraft (Q500 class) +http://www.mh-aerotools.de/airfoils/mh17koo.htm +Characteristics +Thickness: 12.13% +Smaller moment coefficient cm c/4 than e.g. MH 16. +Well suited for the Quickie 500. +Can be used at Reynolds numbers of 400'000 and above. +Developed for lift coefficients between -0.1 and 0.6. +Similar to the MH 16, but with almost zero moment coefficient (benefit: lower load on horizontal tailplane) +See also MH 16, MH 18, MH 18B, MH 20, MH 22, MH 27. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh18b.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh18b.dat new file mode 100644 index 00000000..d112cd5d --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh18b.dat @@ -0,0 +1,68 @@ +MH18B ©Martin Hepperle +1.000000 0.000000 +0.997260 -0.000290 +0.989070 -0.001000 +0.975530 -0.000960 +0.956770 -0.000270 +0.933010 0.001510 +0.904510 0.004780 +0.871570 0.009780 +0.834570 0.016510 +0.793890 0.024750 +0.750000 0.034050 +0.703370 0.043810 +0.654510 0.053330 +0.603960 0.061930 +0.552260 0.069040 +0.500000 0.074240 +0.447740 0.077290 +0.396040 0.078160 +0.345490 0.077000 +0.296630 0.074020 +0.250000 0.069580 +0.206110 0.064010 +0.165430 0.057620 +0.128430 0.050680 +0.095490 0.043430 +0.066990 0.036030 +0.043230 0.028590 +0.024470 0.021210 +0.010930 0.013950 +0.002740 0.006870 +0.000000 0.000000 +0.002740 -0.005480 +0.010930 -0.010420 +0.024470 -0.014870 +0.043230 -0.018910 +0.066990 -0.022620 +0.095490 -0.026050 +0.128430 -0.029230 +0.165430 -0.032110 +0.206110 -0.034620 +0.250000 -0.036670 +0.296630 -0.038160 +0.345490 -0.039000 +0.396040 -0.039180 +0.447740 -0.038710 +0.500000 -0.037660 +0.552260 -0.036130 +0.603960 -0.034210 +0.654510 -0.031970 +0.703370 -0.029480 +0.750000 -0.026770 +0.793890 -0.023820 +0.834570 -0.020660 +0.871570 -0.017300 +0.904510 -0.013810 +0.933010 -0.010320 +0.956770 -0.007010 +0.975530 -0.004110 +0.989070 -0.001820 +0.997260 -0.000450 +1.000000 0.000000 +Thickness: 11.8% +Low moment coefficient of cm c/4. +Well suited for the Quickie 500 (german DMFV B-class). +Optimized version of the MH 18 with improved results for powerful engines. +(Method: geometric optimization with shape functions). +Can be used at Reynoldsnumbers of 350'000 and above. diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh31.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh31.dat new file mode 100644 index 00000000..f3929c53 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh31.dat @@ -0,0 +1,70 @@ +MH31 © Martin Hepperle +1.000000 0.000000 +0.996640 0.000250 +0.986810 0.001130 +0.971040 0.002850 +0.949840 0.005370 +0.923670 0.008580 +0.892990 0.012260 +0.858160 0.016230 +0.819560 0.020310 +0.777550 0.024400 +0.732590 0.028470 +0.685190 0.032440 +0.635900 0.036250 +0.585280 0.039800 +0.533880 0.043010 +0.482270 0.045800 +0.431020 0.048110 +0.380680 0.049850 +0.331810 0.050960 +0.284920 0.051360 +0.240490 0.050980 +0.198970 0.049780 +0.160740 0.047690 +0.126130 0.044680 +0.095420 0.040780 +0.068820 0.036030 +0.046520 0.030470 +0.028570 0.024220 +0.015020 0.017430 +0.005780 0.010420 +0.000870 0.003690 +0.000120 0.001230 +0.000000 -0.000200 +0.000220 -0.001450 +0.000900 -0.002590 +0.002030 -0.003760 +0.006200 -0.006690 +0.017170 -0.011500 +0.033070 -0.015910 +0.053830 -0.019720 +0.079320 -0.022860 +0.109350 -0.025310 +0.143690 -0.027070 +0.182010 -0.028170 +0.223940 -0.028650 +0.269050 -0.028570 +0.316880 -0.027980 +0.366900 -0.026970 +0.418570 -0.025600 +0.471300 -0.023930 +0.524510 -0.022060 +0.577570 -0.020030 +0.629870 -0.017920 +0.680800 -0.015790 +0.729760 -0.013690 +0.776150 -0.011660 +0.819420 -0.009750 +0.859020 -0.007980 +0.894480 -0.006360 +0.925330 -0.004890 +0.951180 -0.003540 +0.971740 -0.002220 +0.986970 -0.000970 +0.996640 -0.000210 +1.000000 0.000000 +Thickness: 7.99% +Well suited for 20% chord flaps. +Can be used at Reynoldsnumbers of 150'000 and above. +At Reynoldsnumbers below 150'000, a turbulator should be placed at 75% chord. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh33.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh33.dat new file mode 100644 index 00000000..84245ab7 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh33.dat @@ -0,0 +1,72 @@ +MH33 © Martin Hepperle +1.000000 0.000000 +0.996770 0.000290 +0.987270 0.001250 +0.971940 0.003020 +0.951250 0.005580 +0.925670 0.008810 +0.895640 0.012460 +0.861500 0.016340 +0.823610 0.020280 +0.782310 0.024160 +0.738040 0.027950 +0.691290 0.031600 +0.642590 0.035030 +0.592470 0.038150 +0.541490 0.040890 +0.490200 0.043200 +0.439140 0.045000 +0.388880 0.046230 +0.339930 0.046840 +0.292810 0.046780 +0.248010 0.046010 +0.205960 0.044490 +0.167060 0.042210 +0.131670 0.039170 +0.100090 0.035390 +0.072580 0.030920 +0.049340 0.025840 +0.030480 0.020250 +0.016110 0.014350 +0.006230 0.008380 +0.000910 0.002810 +0.000340 0.001650 +0.000000 0.000470 +0.000020 -0.000540 +0.000520 -0.001480 +0.001470 -0.002460 +0.006540 -0.005740 +0.017610 -0.010050 +0.033590 -0.014050 +0.054400 -0.017560 +0.079930 -0.020480 +0.109970 -0.022800 +0.144290 -0.024490 +0.182560 -0.025580 +0.224400 -0.026120 +0.269400 -0.026140 +0.317080 -0.025690 +0.366930 -0.024850 +0.418410 -0.023670 +0.470930 -0.022220 +0.523900 -0.020560 +0.576710 -0.018750 +0.628770 -0.016840 +0.679440 -0.014900 +0.728130 -0.012940 +0.774270 -0.011020 +0.817280 -0.009120 +0.856670 -0.007230 +0.892070 -0.005300 +0.923200 -0.003440 +0.949700 -0.001860 +0.971120 -0.000730 +0.986940 -0.000140 +0.996700 -0.000010 +1.000000 0.000000 +Thickness: 7.28% +Moment coefficient of cm c/4 = -0.03. +Well suited for 20% chord flaps (but not absolutely necessary). +Can be used at Reynoldsnumbers of 100'000 and above. +Better performace in the low Cl range than the MH 30 and MH 32, but thinner. +Calculated Polars (PROFIL/Eppler): \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh34.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh34.dat new file mode 100644 index 00000000..75c35ef9 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh34.dat @@ -0,0 +1,73 @@ +MH34 © Martin Hepperle +1.000000 0.000000 +0.996580 0.000400 +0.986660 0.001770 +0.970930 0.004290 +0.950050 0.007810 +0.924540 0.011970 +0.894700 0.016420 +0.860760 0.020950 +0.823060 0.025450 +0.781940 0.029830 +0.737830 0.034050 +0.691240 0.038050 +0.642680 0.041740 +0.592700 0.045060 +0.541830 0.047930 +0.490640 0.050290 +0.439660 0.052060 +0.389460 0.053200 +0.340570 0.053640 +0.293480 0.053350 +0.248690 0.052280 +0.206640 0.050400 +0.167730 0.047710 +0.132320 0.044200 +0.100710 0.039910 +0.073160 0.034880 +0.049850 0.029190 +0.030930 0.022970 +0.016470 0.016400 +0.006490 0.009750 +0.001050 0.003480 +0.000290 0.001650 +0.000010 0.000320 +0.000100 -0.000830 +0.000660 -0.001910 +0.001690 -0.003020 +0.006270 -0.006280 +0.017290 -0.011100 +0.033260 -0.015660 +0.054080 -0.019730 +0.079620 -0.023240 +0.109670 -0.026130 +0.143980 -0.028390 +0.182230 -0.030030 +0.224030 -0.031070 +0.268970 -0.031550 +0.316570 -0.031510 +0.366320 -0.031010 +0.417660 -0.030090 +0.470040 -0.028830 +0.522840 -0.027270 +0.575480 -0.025470 +0.627340 -0.023470 +0.677800 -0.021340 +0.726290 -0.019090 +0.772210 -0.016760 +0.815010 -0.014340 +0.854190 -0.011750 +0.889490 -0.008910 +0.920760 -0.006010 +0.947660 -0.003430 +0.969700 -0.001490 +0.986210 -0.000380 +0.996500 -0.000030 +1.000000 0.000000 +Thickness: 8.51% +Well suited for 20% chord flaps. +Can be used at Reynoldsnumbers of 150'000 and above. +At Reynoldsnumbers below 150'000, a turbulator should be placed at 75% chord. + + + diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh50.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh50.dat new file mode 100644 index 00000000..d4535c0e --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh50.dat @@ -0,0 +1,265 @@ +MH 50 ©Martin Hepperle Very low drag coefficient airfoil for high speed model aircraft +1.00000 0.00000 +0.99982 0.00001 +0.99929 0.00002 +0.99839 0.00004 +0.99713 0.00008 +0.99552 0.00014 +0.99357 0.00021 +0.99126 0.00030 +0.98860 0.00042 +0.98560 0.00058 +0.98227 0.00078 +0.97860 0.00099 +0.97460 0.00126 +0.97028 0.00157 +0.96565 0.00191 +0.96071 0.00231 +0.95546 0.00275 +0.94992 0.00324 +0.94409 0.00378 +0.93798 0.00436 +0.93160 0.00501 +0.92496 0.00571 +0.91808 0.00646 +0.91095 0.00726 +0.90361 0.00810 +0.89606 0.00898 +0.88832 0.00987 +0.88036 0.01077 +0.87221 0.01167 +0.86385 0.01257 +0.85530 0.01347 +0.84655 0.01436 +0.83760 0.01524 +0.82846 0.01613 +0.81913 0.01699 +0.80961 0.01784 +0.79991 0.01869 +0.79003 0.01953 +0.77997 0.02036 +0.76974 0.02118 +0.75937 0.02201 +0.74885 0.02283 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end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh51.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh51.dat new file mode 100644 index 00000000..fefeaf8b --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh51.dat @@ -0,0 +1,266 @@ +MH 51 ©Martin Hepperle Very low drag coefficient airfoil for high speed model aircraft +1.00000 0.00000 +0.99981 0.00000 +0.99926 0.00002 +0.99835 0.00006 +0.99709 0.00011 +0.99548 0.00017 +0.99351 0.00025 +0.99120 0.00036 +0.98853 0.00048 +0.98553 0.00063 +0.98218 0.00081 +0.97850 0.00102 +0.97448 0.00127 +0.97014 0.00154 +0.96548 0.00186 +0.96050 0.00222 +0.95521 0.00262 +0.94962 0.00307 +0.94373 0.00356 +0.93755 0.00409 +0.93109 0.00467 +0.92435 0.00529 +0.91734 0.00597 +0.91007 0.00668 +0.90255 0.00745 +0.89478 0.00827 +0.88679 0.00913 +0.87857 0.01005 +0.87014 0.01101 +0.86151 0.01201 +0.85271 0.01304 +0.84372 0.01412 +0.83458 0.01522 +0.82530 0.01633 +0.81587 0.01745 +0.80630 0.01855 +0.79658 0.01963 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about 1'300'000. +Ideal chord length about c[m] = 67 / v[km/h]. +more maximum lift than MH 50. diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh52.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh52.dat new file mode 100644 index 00000000..04c44825 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh52.dat @@ -0,0 +1,266 @@ +MH 52 ©Martin Hepperle Very low drag coefficient airfoil for high speed model aircraft +1.00000 0.00000 +0.99982 0.00001 +0.99927 0.00002 +0.99836 0.00006 +0.99710 0.00010 +0.99550 0.00017 +0.99355 0.00026 +0.99124 0.00037 +0.98859 0.00051 +0.98560 0.00068 +0.98227 0.00089 +0.97861 0.00115 +0.97463 0.00144 +0.97032 0.00179 +0.96570 0.00218 +0.96077 0.00261 +0.95553 0.00312 +0.95000 0.00367 +0.94419 0.00427 +0.93808 0.00492 +0.93171 0.00563 +0.92507 0.00639 +0.91818 0.00720 +0.91104 0.00807 +0.90367 0.00897 +0.89608 0.00993 +0.88828 0.01091 +0.88028 0.01191 +0.87210 0.01295 +0.86374 0.01399 +0.85521 0.01502 +0.84651 0.01605 +0.83765 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+http://www.mh-aerotools.de/airfoils/mh52koo.htm +Characteristics +Thickness: 9.00% +Camber: -0.1% +The ideal Reynoldsnumber is about 1'500'000. +Ideal chord length about c[m] = 77 / v[km/h]. +Thicker than MH 51, only slightly more drag. diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh53.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh53.dat new file mode 100644 index 00000000..7cec4f81 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh53.dat @@ -0,0 +1,267 @@ +MH 53 ©Martin Hepperle Very low drag coefficient airfoil for high speed model aircr +1.00000 0.00000 +0.99980 0.00001 +0.99920 0.00003 +0.99822 0.00007 +0.99686 0.00014 +0.99511 0.00023 +0.99299 0.00036 +0.99050 0.00054 +0.98764 0.00077 +0.98442 0.00105 +0.98084 0.00140 +0.97693 0.00180 +0.97268 0.00227 +0.96809 0.00281 +0.96320 0.00341 +0.95801 0.00407 +0.95251 0.00480 +0.94672 0.00558 +0.94066 0.00643 +0.93434 0.00732 +0.92775 0.00826 +0.92092 0.00925 +0.91386 0.01028 +0.90659 0.01134 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-0.00037 +0.99689 -0.00022 +0.99824 -0.00011 +0.99921 -0.00005 +0.99980 -0.00001 +1.00000 0.00000 + +http://www.mh-aerotools.de/airfoils/mh53koo.htm +Characteristics +Thickness: 9.43% +Camber: 0.4% +The ideal Reynolds number is about 1'800'000. +Ideal chord length about c[m] = 92 / v[km/h]. +Very low drag if you reach beyond Re=1'500'000. +Could also be of interest for F3D pylon racing models. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mh54.dat b/aerosandbox/geometry/airfoil/airfoil_database/mh54.dat new file mode 100644 index 00000000..321302a2 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mh54.dat @@ -0,0 +1,265 @@ +MH 54 ©Martin Hepperle Very low drag coefficient airfoil for high speed model aircraft +1.00000 0.00000 +0.99924 0.00004 +0.99830 0.00008 +0.99699 0.00014 +0.99532 0.00022 +0.99329 0.00034 +0.99089 0.00048 +0.98815 0.00067 +0.98506 0.00089 +0.98162 0.00117 +0.97785 0.00149 +0.97375 0.00186 +0.96933 0.00229 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b/aerosandbox/geometry/airfoil/airfoil_database/mid021.dat @@ -0,0 +1,129 @@ +MID 021 (c)Slobodan Midic for Hand and Catapult Launched Glider + 1.000000 0.002041 + 0.990271 0.002919 + 0.970203 0.004882 + 0.947705 0.007255 + 0.924730 0.009726 + 0.901863 0.012094 + 0.878985 0.014341 + 0.856030 0.016481 + 0.833032 0.018524 + 0.810033 0.020458 + 0.787024 0.022282 + 0.763989 0.023995 + 0.740919 0.025595 + 0.717825 0.027090 + 0.694705 0.028474 + 0.671566 0.029753 + 0.648397 0.030927 + 0.625214 0.031994 + 0.602013 0.032959 + 0.578797 0.033820 + 0.555562 0.034581 + 0.532314 0.035243 + 0.509052 0.035807 + 0.485780 0.036272 + 0.462483 0.036643 + 0.439185 0.036922 + 0.415879 0.037110 + 0.392570 0.037205 + 0.369267 0.037213 + 0.346025 0.037118 + 0.322842 0.036913 + 0.299732 0.036582 + 0.276720 0.036105 + 0.253791 0.035469 + 0.230952 0.034659 + 0.208213 0.033669 + 0.185618 0.032475 + 0.163222 0.031051 + 0.141077 0.029374 + 0.119290 0.027403 + 0.098049 0.025106 + 0.077670 0.022418 + 0.058424 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-0,0 +1,131 @@ +MID 022 (c)Slobodan Midic for Hand and Catapult Launched Glider + 1.000000 0.002645 + 0.990274 0.003716 + 0.970206 0.006104 + 0.947707 0.008979 + 0.924732 0.011967 + 0.901865 0.014828 + 0.878987 0.017536 + 0.856032 0.020116 + 0.833035 0.022571 + 0.810035 0.024893 + 0.787027 0.027077 + 0.763991 0.029123 + 0.740921 0.031031 + 0.717828 0.032805 + 0.694708 0.034443 + 0.671568 0.035951 + 0.648399 0.037326 + 0.625217 0.038572 + 0.602016 0.039691 + 0.578799 0.040683 + 0.555564 0.041554 + 0.532317 0.042305 + 0.509054 0.042940 + 0.485782 0.043457 + 0.462486 0.043864 + 0.439187 0.044164 + 0.415881 0.044359 + 0.392572 0.044448 + 0.369269 0.044438 + 0.346027 0.044314 + 0.322845 0.044063 + 0.299734 0.043670 + 0.276721 0.043113 + 0.253793 0.042372 + 0.230953 0.041422 + 0.208214 0.040258 + 0.185621 0.038848 + 0.163225 0.037168 + 0.141080 0.035183 + 0.119292 0.032850 + 0.098051 0.030127 + 0.077671 0.026933 + 0.058425 0.023162 + 0.040574 0.018746 + 0.025124 0.014020 + 0.014299 0.009990 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Slobodan Midic Re~10k-40k HLGlider + 1.000000 0.002116 + 0.996644 0.002492 + 0.988506 0.003420 + 0.977818 0.004681 + 0.966622 0.006052 + 0.955333 0.007472 + 0.943965 0.008925 + 0.932587 0.010380 + 0.921276 0.011805 + 0.910001 0.013190 + 0.898726 0.014535 + 0.887438 0.015843 + 0.876133 0.017118 + 0.864816 0.018361 + 0.853488 0.019573 + 0.842157 0.020755 + 0.830825 0.021908 + 0.819492 0.023029 + 0.808158 0.024118 + 0.796824 0.025174 + 0.785484 0.026200 + 0.774139 0.027195 + 0.762793 0.028158 + 0.751445 0.029090 + 0.740086 0.029993 + 0.728723 0.030866 + 0.717362 0.031710 + 0.705997 0.032524 + 0.694622 0.033310 + 0.683244 0.034068 + 0.671870 0.034799 + 0.660492 0.035501 + 0.649105 0.036175 + 0.637715 0.036824 + 0.626330 0.037446 + 0.614945 0.038039 + 0.603554 0.038606 + 0.592159 0.039146 + 0.580764 0.039659 + 0.569368 0.040146 + 0.557966 0.040608 + 0.546563 0.041044 + 0.535161 0.041454 + 0.523759 0.041839 + 0.512353 0.042197 + 0.500946 0.042530 + 0.489541 0.042838 + 0.478134 0.043121 + 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+ 0.977692 0.000085 + 0.988492 -0.000854 + 0.996691 -0.001584 + 1.000000 -0.001883 + +*modification tracfoil 0.999975->1.000000 0.002116 / 1.000030->1.000000 -0.001883 + +MID 027 5% +---------------- + +Aero profil MID 027 ima debljinu od 5%, krivinu od 2.5%, +radijus zaobljenja napadne ivice od 0.3%, debljinu izlazne +ivice od 0.4%. Namenjen je za sobne klizace F1N za +kategorije visina hala 3 i 4. Maximalni koeficijent uzgona +pri Re brojevima od 10k do 40k je oko Cz=0.6. Dobre su +mu i karakteristike za vertikalno izbacivanje jer ima mali +koef. otpora Cx pri nultom koef. uzgona Cz=0, +odnosno: Cxo=0.011. + +Novi Sad, 13.jan.2010. +Slobodan Midic \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid029.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid029.dat new file mode 100644 index 00000000..935dbb5e --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid029.dat @@ -0,0 +1,161 @@ +MID 29 (c)Slobodan Midic RC flying gliders for slow and speed gliding + 1.000000 0.000347 + 0.994054 0.001160 + 0.982050 0.002901 + 0.968503 0.004903 + 0.954662 0.006968 + 0.940783 0.009035 + 0.926901 0.011086 + 0.913016 0.013114 + 0.899128 0.015117 + 0.885240 0.017096 + 0.871350 0.019051 + 0.857464 0.020981 + 0.843575 0.022888 + 0.829689 0.024771 + 0.815801 0.026627 + 0.801909 0.028458 + 0.788021 0.030260 + 0.774128 0.032032 + 0.760232 0.033773 + 0.746336 0.035485 + 0.732435 0.037159 + 0.718530 0.038802 + 0.704627 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+++ b/aerosandbox/geometry/airfoil/airfoil_database/mid101.dat @@ -0,0 +1,144 @@ +MID 101 7.7% for F1A as low drag airfoils (c) Slobodan Midic + 1.000000 0.002381 + 0.993208 0.003626 + 0.979610 0.006143 + 0.963818 0.009076 + 0.947499 0.012112 + 0.931119 0.015174 + 0.914749 0.018251 + 0.898420 0.021331 + 0.882178 0.024340 + 0.865951 0.027257 + 0.849694 0.030094 + 0.833414 0.032860 + 0.817127 0.035549 + 0.800838 0.038158 + 0.784553 0.040682 + 0.768267 0.043117 + 0.751981 0.045457 + 0.735690 0.047701 + 0.719387 0.049847 + 0.703074 0.051894 + 0.686745 0.053843 + 0.670402 0.055696 + 0.654043 0.057453 + 0.637670 0.059116 + 0.621283 0.060687 + 0.604883 0.062166 + 0.588475 0.063554 + 0.572060 0.064852 + 0.555635 0.066060 + 0.539206 0.067177 + 0.522772 0.068204 + 0.506334 0.069138 + 0.489899 0.069983 + 0.473466 0.070731 + 0.457035 0.071381 + 0.440615 0.071930 + 0.424202 0.072373 + 0.407800 0.072708 + 0.391415 0.072931 + 0.375041 0.073035 + 0.358685 0.073018 + 0.342348 0.072872 + 0.326030 0.072594 + 0.309740 0.072176 + 0.293467 0.071611 + 0.277227 0.070900 + 0.261031 0.070031 + 0.244873 0.068998 + 0.228768 0.067791 + 0.212713 0.066401 + 0.196716 0.064819 + 0.180776 0.063033 + 0.164904 0.061042 + 0.149137 0.058833 + 0.133523 0.056395 + 0.118158 0.053704 + 0.103147 0.050725 + 0.088615 0.047401 + 0.074696 0.043678 + 0.061408 0.039453 + 0.048799 0.034697 + 0.036905 0.029376 + 0.026078 0.023753 + 0.017350 0.018592 + 0.011208 0.014428 + 0.007102 0.011123 + 0.004318 0.008342 + 0.002380 0.005935 + 0.001047 0.003792 + 0.000252 0.001803 + 0.000000 -0.000050 + 0.000313 -0.001885 + 0.001307 -0.003684 + 0.003002 -0.005328 + 0.005393 -0.006888 + 0.008584 -0.008537 + 0.012920 -0.010342 + 0.018967 -0.012327 + 0.027424 -0.014410 + 0.038729 -0.016253 + 0.052342 -0.017478 + 0.067274 -0.018060 + 0.082597 -0.018259 + 0.097992 -0.018184 + 0.113491 -0.017837 + 0.129183 -0.017225 + 0.145106 -0.016363 + 0.161264 -0.015262 + 0.177605 -0.013943 + 0.194052 -0.012427 + 0.210525 -0.010747 + 0.226981 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of 7.7% and camber of 4.5% of cord. +modif tracfoil ->1.000000 Slobodan Midic xfoil@yahoogroups.com \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid101tip.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid101tip.dat new file mode 100644 index 00000000..46c7c93d --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid101tip.dat @@ -0,0 +1,144 @@ +MID 101 tip Wing tip for F1A as low drag airfoils (c) Slobodan Midic + 1.000000 0.002244 + 0.993727 0.003520 + 0.980238 0.006022 + 0.964546 0.008824 + 0.948300 0.011601 + 0.931961 0.014269 + 0.915604 0.016833 + 0.899261 0.019304 + 0.882994 0.021675 + 0.866735 0.023953 + 0.850437 0.026145 + 0.834109 0.028247 + 0.817766 0.030259 + 0.801416 0.032185 + 0.785067 0.034040 + 0.768720 0.035836 + 0.752379 0.037584 + 0.736042 0.039299 + 0.719703 0.040992 + 0.703365 0.042676 + 0.687019 0.044355 + 0.670662 0.046007 + 0.654290 0.047606 + 0.637903 0.049124 + 0.621504 0.050534 + 0.605091 0.051809 + 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0.768914 0.017330 + 0.785187 0.016668 + 0.801451 0.015891 + 0.817707 0.014997 + 0.833961 0.013992 + 0.850207 0.012876 + 0.866446 0.011652 + 0.882675 0.010321 + 0.898906 0.008883 + 0.915128 0.007345 + 0.931343 0.005706 + 0.947543 0.003972 + 0.963665 0.002158 + 0.979286 0.000319 + 0.992797 -0.001333 + 1.000000 -0.002181 + +MID 101 tip has thickness of 7.0% and camber of 3.5% of cord. +modif tracfoil ->1.000000 Slobodan Midic xfoil@yahoogroups.com \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid102.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid102.dat new file mode 100644 index 00000000..85dd7a88 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid102.dat @@ -0,0 +1,201 @@ +MID 102 #Slobodan Midic for F1A as LDA + 1.000000 0.002642 + 0.996570 0.003272 + 0.989491 0.004615 + 0.979788 0.006516 + 0.968792 0.008745 + 0.956842 0.011244 + 0.944421 0.013881 + 0.931998 0.016512 + 0.919714 0.019067 + 0.907511 0.021530 + 0.895308 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00000000..fce9d1db --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid102tip.dat @@ -0,0 +1,201 @@ +MID-102-tip #Slobodan Midic for F1A as LDA + 1.000000 0.002478 + 0.996892 0.002904 + 0.989811 0.003814 + 0.980105 0.005115 + 0.969105 0.006658 + 0.957151 0.008403 + 0.944726 0.010259 + 0.932299 0.012120 + 0.920011 0.013933 + 0.907804 0.015684 + 0.895597 0.017382 + 0.883346 0.019034 + 0.871050 0.020645 + 0.858712 0.022219 + 0.846337 0.023760 + 0.833959 0.025263 + 0.821583 0.026728 + 0.809207 0.028153 + 0.796830 0.029537 + 0.784438 0.030882 + 0.772029 0.032191 + 0.759610 0.033462 + 0.747177 0.034696 + 0.734720 0.035896 + 0.722257 0.037062 + 0.709792 0.038192 + 0.697314 0.039288 + 0.684823 0.040351 + 0.672321 0.041380 + 0.659814 0.042377 + 0.647299 0.043342 + 0.634766 0.044275 + 0.622224 0.045176 + 0.609692 0.046045 + 0.597157 0.046878 + 0.584598 0.047679 + 0.572035 0.048448 + 0.559475 0.049184 + 0.546902 0.049885 + 0.534315 0.050555 + 0.521736 0.051190 + 0.509154 0.051792 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0.007596 + 0.906764 0.006627 + 0.919058 0.005605 + 0.931358 0.004532 + 0.943641 0.003407 + 0.955898 0.002229 + 0.967930 0.001014 + 0.979147 -0.000173 + 0.989097 -0.001270 + 0.996284 -0.002089 + 1.000000 -0.002486 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid103.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid103.dat new file mode 100644 index 00000000..32a5f283 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid103.dat @@ -0,0 +1,232 @@ +MID 103 7% c) Slobodan Midic low speed Re numbers from 40,000 and more + 1.000000 0.002500 + 0.996570 0.003080 + 0.989491 0.004314 + 0.979788 0.006063 + 0.968792 0.008117 + 0.956842 0.010419 + 0.944421 0.012851 + 0.931998 0.015278 + 0.919714 0.017635 + 0.907511 0.019908 + 0.895308 0.022108 + 0.883061 0.024244 + 0.870769 0.026322 + 0.858435 0.028345 + 0.846064 0.030318 + 0.833690 0.032235 + 0.821318 0.034095 + 0.808946 0.035896 + 0.796573 0.037637 + 0.784185 0.039320 + 0.771780 0.040948 + 0.759365 0.042519 + 0.746936 0.044034 + 0.734483 0.045497 + 0.722024 0.046906 + 0.709563 0.048261 + 0.697089 0.049562 + 0.684602 0.050812 + 0.672104 0.052009 + 0.659601 0.053155 + 0.647090 0.054250 + 0.634561 0.055295 + 0.622023 0.056291 + 0.609495 0.057237 + 0.596964 0.058130 + 0.584409 0.058975 + 0.571850 0.059773 + 0.559294 0.060521 + 0.546725 0.061220 + 0.534143 0.061874 + 0.521568 0.062479 + 0.508990 0.063037 + 0.496399 0.063548 + 0.483797 0.064013 + 0.471188 0.064434 + 0.458582 0.064810 + 0.445964 0.065141 + 0.433340 0.065429 + 0.420734 0.065673 + 0.408124 0.065870 + 0.395489 0.066024 + 0.382855 0.066138 + 0.370253 0.066207 + 0.357684 0.066228 + 0.345141 0.066197 + 0.332634 0.066110 + 0.320167 0.065964 + 0.307730 0.065753 + 0.295331 0.065476 + 0.282988 0.065127 + 0.270700 0.064699 + 0.258448 0.064187 + 0.246227 0.063588 + 0.234049 0.062900 + 0.221921 0.062118 + 0.209846 0.061238 + 0.197838 0.060256 + 0.185898 0.059165 + 0.174043 0.057961 + 0.162297 0.056638 + 0.150656 0.055186 + 0.139142 0.053600 + 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0.051061 -0.015959 + 0.061014 -0.016210 + 0.071827 -0.016237 + 0.083286 -0.016079 + 0.095145 -0.015778 + 0.107161 -0.015363 + 0.119166 -0.014836 + 0.131245 -0.014191 + 0.143475 -0.013440 + 0.155843 -0.012601 + 0.168311 -0.011692 + 0.180837 -0.010726 + 0.193412 -0.009707 + 0.206051 -0.008643 + 0.218743 -0.007542 + 0.231441 -0.006413 + 0.244159 -0.005254 + 0.256911 -0.004070 + 0.269682 -0.002863 + 0.282481 -0.001638 + 0.295306 -0.000397 + 0.308157 0.000855 + 0.321033 0.002115 + 0.333914 0.003379 + 0.346784 0.004641 + 0.359636 0.005896 + 0.372468 0.007140 + 0.385277 0.008371 + 0.398060 0.009584 + 0.410821 0.010777 + 0.423553 0.011946 + 0.436257 0.013086 + 0.448947 0.014197 + 0.461612 0.015274 + 0.474249 0.016314 + 0.486863 0.017313 + 0.499458 0.018269 + 0.512034 0.019180 + 0.524580 0.020041 + 0.537101 0.020849 + 0.549609 0.021602 + 0.562098 0.022297 + 0.574564 0.022931 + 0.587003 0.023502 + 0.599418 0.024005 + 0.611818 0.024439 + 0.624191 0.024801 + 0.636544 0.025087 + 0.648879 0.025296 + 0.661190 0.025424 + 0.673486 0.025471 + 0.685780 0.025433 + 0.698073 0.025313 + 0.710364 0.025109 + 0.722657 0.024822 + 0.734953 0.024452 + 0.747251 0.024001 + 0.759542 0.023468 + 0.771827 0.022853 + 0.784123 0.022154 + 0.796423 0.021377 + 0.808708 0.020519 + 0.820996 0.019581 + 0.833289 0.018563 + 0.845583 0.017467 + 0.857874 0.016294 + 0.870161 0.015044 + 0.882452 0.013717 + 0.894753 0.012314 + 0.907057 0.010839 + 0.919355 0.009292 + 0.931659 0.007674 + 0.943946 0.005989 + 0.956207 0.004242 + 0.968243 0.002466 + 0.979464 0.000757 + 0.989417 -0.000800 + 0.996606 -0.001948 + 1.000000 -0.002500 + +*modification 0.999975->1.000000 0.002500 / 1.000025->1.000000 -0.002500 + +MID 103 7% +=========== + +This airfoil has thickness of 7%, and camber of 4.1%. +It is intended for all free flite (FF) airplane models for low +speed with Re numbers from 40,000 and more. + +Airfoil must have appropriate turbulators at the top and/or +bootom side to provide turbulent flow on up side from +30% of cord and on down side from 5% of cord. By some +models, they fly only with higher lift, turbulator on the bottom +side is not need, so the drag is lower. To make turbulators +more effective at small Re numbers, on the top side invigators +after 50% of cord are welcome. + +Because of relative thin thickness of 7% it must build wing +of a high aspect ratio in a modern high technology mode. + +Drag coeficient CD at zero lift CL=0 is very small in +comparison with usualy airfoils wit high cambers, so +the model can be suitable for succesfull vertical launching. + +The airfoil is suitable for all FAI FF classis of flying models: +F1ABCE.... + +Slobodan Midic + +Novi Sad, Jan. 2010. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid103bc45.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid103bc45.dat new file mode 100644 index 00000000..4ab3937f --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid103bc45.dat @@ -0,0 +1,204 @@ +MID 103b c45 for wing root + 1.000000 0.002642 + 0.996570 0.003272 + 0.989491 0.004615 + 0.979788 0.006516 + 0.968792 0.008745 + 0.956842 0.011244 + 0.944421 0.013881 + 0.931998 0.016512 + 0.919714 0.019067 + 0.907511 0.021530 + 0.895308 0.023914 + 0.883061 0.026227 + 0.870769 0.028478 + 0.858435 0.030668 + 0.846064 0.032804 + 0.833690 0.034879 + 0.821318 0.036891 + 0.808946 0.038838 + 0.796573 0.040719 + 0.784185 0.042537 + 0.771780 0.044295 + 0.759365 0.045990 + 0.746936 0.047624 + 0.734483 0.049200 + 0.722024 0.050718 + 0.709563 0.052176 + 0.697089 0.053574 + 0.684602 0.054917 + 0.672104 0.056201 + 0.659601 0.057430 + 0.647090 0.058601 + 0.634561 0.059719 + 0.622023 0.060781 + 0.609495 0.061790 + 0.596964 0.062739 + 0.584409 0.063638 + 0.571850 0.064484 + 0.559294 0.065275 + 0.546725 0.066012 + 0.534143 0.066702 + 0.521568 0.067337 + 0.508990 0.067921 + 0.496399 0.068453 + 0.483797 0.068937 + 0.471188 0.069372 + 0.458582 0.069758 + 0.445964 0.070096 + 0.433340 0.070386 + 0.420734 0.070628 + 0.408124 0.070821 + 0.395489 0.070966 + 0.382855 0.071068 + 0.370253 0.071123 + 0.357684 0.071125 + 0.345141 0.071072 + 0.332634 0.070958 + 0.320167 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0.001909 -0.004541 + 0.002665 -0.005259 + 0.003553 -0.005972 + 0.004577 -0.006698 + 0.005756 -0.007445 + 0.007119 -0.008226 + 0.008710 -0.009050 + 0.010580 -0.009927 + 0.012796 -0.010841 + 0.015461 -0.011773 + 0.018738 -0.012715 + 0.022838 -0.013666 + 0.027977 -0.014588 + 0.034350 -0.015422 + 0.042090 -0.016102 + 0.051061 -0.016567 + 0.061014 -0.016780 + 0.071827 -0.016755 + 0.083286 -0.016536 + 0.095145 -0.016168 + 0.107161 -0.015684 + 0.119166 -0.015082 + 0.131245 -0.014358 + 0.143475 -0.013522 + 0.155843 -0.012596 + 0.168311 -0.011597 + 0.180837 -0.010538 + 0.193412 -0.009425 + 0.206051 -0.008267 + 0.218743 -0.007070 + 0.231441 -0.005846 + 0.244159 -0.004590 + 0.256911 -0.003310 + 0.269682 -0.002006 + 0.282481 -0.000685 + 0.295306 0.000652 + 0.308157 0.002000 + 0.321033 0.003354 + 0.333914 0.004712 + 0.346784 0.006067 + 0.359636 0.007414 + 0.372468 0.008748 + 0.385277 0.010067 + 0.398060 0.011365 + 0.410821 0.012642 + 0.423553 0.013892 + 0.436257 0.015111 + 0.448947 0.016298 + 0.461612 0.017447 + 0.474249 0.018556 + 0.486863 0.019620 + 0.499458 0.020638 + 0.512034 0.021606 + 0.524580 0.022521 + 0.537101 0.023377 + 0.549609 0.024175 + 0.562098 0.024908 + 0.574564 0.025576 + 0.587003 0.026174 + 0.599418 0.026700 + 0.611818 0.027152 + 0.624191 0.027523 + 0.636544 0.027814 + 0.648879 0.028021 + 0.661190 0.028141 + 0.673486 0.028173 + 0.685780 0.028113 + 0.698073 0.027964 + 0.710364 0.027723 + 0.722657 0.027393 + 0.734953 0.026973 + 0.747251 0.026466 + 0.759542 0.025871 + 0.771827 0.025185 + 0.784123 0.024408 + 0.796423 0.023548 + 0.808708 0.022599 + 0.820996 0.021564 + 0.833289 0.020442 + 0.845583 0.019234 + 0.857874 0.017945 + 0.870161 0.016571 + 0.882452 0.015114 + 0.894753 0.013573 + 0.907057 0.011956 + 0.919355 0.010259 + 0.931659 0.008484 + 0.943946 0.006638 + 0.956207 0.004725 + 0.968243 0.002781 + 0.979464 0.000913 + 0.989417 -0.000786 + 0.996606 -0.002037 + 1.000000 -0.002640 + +airfoil MID-103b-c45, with thickness of 7.3%c and camber of 4.5%c,is +intended for wing root \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid103c3.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid103c3.dat new file mode 100644 index 00000000..07c77164 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid103c3.dat @@ -0,0 +1,204 @@ +MID 103 c3 Airfoil for wing tip + 1.000000 0.002478 + 0.996892 0.002904 + 0.989811 0.003814 + 0.980105 0.005115 + 0.969105 0.006658 + 0.957151 0.008403 + 0.944726 0.010259 + 0.932299 0.012120 + 0.920011 0.013933 + 0.907804 0.015684 + 0.895597 0.017382 + 0.883346 0.019034 + 0.871050 0.020645 + 0.858712 0.022219 + 0.846337 0.023760 + 0.833959 0.025263 + 0.821583 0.026728 + 0.809207 0.028153 + 0.796830 0.029537 + 0.784438 0.030882 + 0.772029 0.032191 + 0.759610 0.033462 + 0.747177 0.034696 + 0.734720 0.035896 + 0.722257 0.037062 + 0.709792 0.038192 + 0.697314 0.039288 + 0.684823 0.040351 + 0.672321 0.041380 + 0.659814 0.042377 + 0.647299 0.043342 + 0.634766 0.044275 + 0.622224 0.045176 + 0.609692 0.046045 + 0.597157 0.046878 + 0.584598 0.047679 + 0.572035 0.048448 + 0.559475 0.049184 + 0.546902 0.049885 + 0.534315 0.050555 + 0.521736 0.051190 + 0.509154 0.051792 + 0.496559 0.052360 + 0.483953 0.052894 + 0.471340 0.053395 + 0.458730 0.053863 + 0.446108 0.054297 + 0.433480 0.054699 + 0.420870 0.055065 + 0.408256 0.055395 + 0.395617 0.055690 + 0.382979 0.055954 + 0.370373 0.056180 + 0.357799 0.056365 + 0.345252 0.056507 + 0.332741 0.056600 + 0.320270 0.056642 + 0.307829 0.056627 + 0.295426 0.056553 + 0.283079 0.056416 + 0.270787 0.056208 + 0.258531 0.055926 + 0.246306 0.055565 + 0.234125 0.055124 + 0.221993 0.054598 + 0.209914 0.053983 + 0.197902 0.053276 + 0.185958 0.052469 + 0.174099 0.051559 + 0.162349 0.050538 + 0.150705 0.049398 + 0.139187 0.048133 + 0.127825 0.046735 + 0.116641 0.045195 + 0.105688 0.043508 + 0.095041 0.041672 + 0.084751 0.039680 + 0.074856 0.037521 + 0.065407 0.035188 + 0.056390 0.032660 + 0.047770 0.029918 + 0.039634 0.027000 + 0.032147 0.023988 + 0.025595 0.021050 + 0.020253 0.018393 + 0.016068 0.016083 + 0.012799 0.014097 + 0.010233 0.012403 + 0.008195 0.010952 + 0.006547 0.009687 + 0.005195 0.008559 + 0.004072 0.007529 + 0.003133 0.006571 + 0.002350 0.005664 + 0.001700 0.004797 + 0.001168 0.003956 + 0.000745 0.003138 + 0.000420 0.002337 + 0.000190 0.001558 + 0.000051 0.000807 + -0.000001 0.000073 + 0.000037 -0.000652 + 0.000173 -0.001388 + 0.000419 -0.002164 + 0.000789 -0.002938 + 0.001284 -0.003701 + 0.001908 -0.004442 + 0.002664 -0.005164 + 0.003552 -0.005891 + 0.004576 -0.006631 + 0.005754 -0.007395 + 0.007117 -0.008197 + 0.008707 -0.009049 + 0.010577 -0.009962 + 0.012792 -0.010931 + 0.015456 -0.011943 + 0.018732 -0.013004 + 0.022831 -0.014117 + 0.027968 -0.015262 + 0.034339 -0.016393 + 0.042076 -0.017448 + 0.051044 -0.018348 + 0.060994 -0.019034 + 0.071804 -0.019503 + 0.083259 -0.019778 + 0.095114 -0.019892 + 0.107126 -0.019869 + 0.119127 -0.019713 + 0.131203 -0.019427 + 0.143429 -0.019025 + 0.155793 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0.014123 + 0.783869 0.013741 + 0.796165 0.013299 + 0.808447 0.012796 + 0.820731 0.012231 + 0.833020 0.011606 + 0.845310 0.010921 + 0.857597 0.010177 + 0.869880 0.009374 + 0.882167 0.008513 + 0.894464 0.007596 + 0.906764 0.006627 + 0.919058 0.005605 + 0.931358 0.004532 + 0.943641 0.003407 + 0.955898 0.002229 + 0.967930 0.001014 + 0.979147 -0.000173 + 0.989097 -0.001270 + 0.996284 -0.002089 + 1.000000 -0.002486 + +Airfoil at wing tip is intended MID-103-c3, with thickness of 6.9%c, +and camber of 3%c. All wing is planparallel except last 100-150mm of tip, \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid104.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid104.dat new file mode 100644 index 00000000..ea502cf4 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid104.dat @@ -0,0 +1,209 @@ +MID 104 #Donjaka MID 103+Gornjaka MID 106 free flite (FF) + 1.000000 0.002555 + 0.996400 0.003213 + 0.989184 0.004552 + 0.979395 0.006370 + 0.967776 0.008538 + 0.955429 0.010851 + 0.942891 0.013203 + 0.930278 0.015586 + 0.917685 0.017975 + 0.905133 0.020378 + 0.892653 0.022751 + 0.880248 0.025068 + 0.867869 0.027327 + 0.855439 0.029546 + 0.843007 0.031723 + 0.830555 0.033858 + 0.818092 0.035953 + 0.805656 0.037999 + 0.793221 0.039995 + 0.780781 0.041945 + 0.768369 0.043839 + 0.755959 0.045676 + 0.743533 0.047463 + 0.731132 0.049190 + 0.718715 0.050860 + 0.706282 0.052476 + 0.693848 0.054038 + 0.681412 0.055540 + 0.668953 0.056990 + 0.656483 0.058387 + 0.644016 0.059729 + 0.631536 0.061016 + 0.619026 0.062254 + 0.606523 0.063440 + 0.594025 0.064571 + 0.581506 0.065651 + 0.568979 0.066680 + 0.556460 0.067657 + 0.543943 0.068579 + 0.531406 0.069450 + 0.518870 0.070270 + 0.506354 0.071035 + 0.493830 0.071744 + 0.481301 0.072400 + 0.468788 0.073001 + 0.456293 0.073541 + 0.443791 0.074023 + 0.431300 0.074446 + 0.418836 0.074806 + 0.406387 0.075099 + 0.393937 0.075327 + 0.381507 0.075488 + 0.369117 0.075576 + 0.356723 0.075590 + 0.344344 0.075531 + 0.332006 0.075395 + 0.319687 0.075176 + 0.307378 0.074875 + 0.295094 0.074490 + 0.282854 0.074018 + 0.270635 0.073455 + 0.258457 0.072798 + 0.246328 0.072045 + 0.234241 0.071187 + 0.222187 0.070225 + 0.210204 0.069155 + 0.198255 0.067967 + 0.186349 0.066662 + 0.174507 0.065239 + 0.162722 0.063689 + 0.151025 0.062017 + 0.139466 0.060218 + 0.128074 0.058285 + 0.116931 0.056220 + 0.106100 0.054008 + 0.095628 0.051641 + 0.085588 0.049110 + 0.076014 0.046398 + 0.066887 0.043474 + 0.058148 0.040314 + 0.049846 0.036935 + 0.041950 0.033305 + 0.034463 0.029469 + 0.027659 0.025631 + 0.021867 0.022090 + 0.017276 0.019071 + 0.013737 0.016571 + 0.010998 0.014505 + 0.008848 0.012757 + 0.007129 0.011226 + 0.005729 0.009853 + 0.004569 0.008606 + 0.003595 0.007465 + 0.002770 0.006413 + 0.002071 0.005433 + 0.001484 0.004511 + 0.001001 0.003635 + 0.000614 0.002796 + 0.000320 0.001985 + 0.000121 0.001204 + 0.000018 0.000459 + 0.000036 -0.000634 + 0.000172 -0.001369 + 0.000418 -0.002118 + 0.000788 -0.002868 + 0.001283 -0.003600 + 0.001908 -0.004303 + 0.002664 -0.004985 + 0.003552 -0.005666 + 0.004576 -0.006359 + 0.005755 -0.007072 + 0.007118 -0.007818 + 0.008709 -0.008606 + 0.010579 -0.009444 + 0.012795 -0.010321 + 0.015460 -0.011216 + 0.018737 -0.012126 + 0.022837 -0.013048 + 0.027976 -0.013948 + 0.034349 -0.014772 + 0.042089 -0.015459 + 0.051060 -0.015946 + 0.061013 -0.016197 + 0.071826 -0.016224 + 0.083285 -0.016066 + 0.095144 -0.015765 + 0.107160 -0.015350 + 0.119165 -0.014823 + 0.131244 -0.014178 + 0.143474 -0.013427 + 0.155842 -0.012588 + 0.168310 -0.011679 + 0.180836 -0.010713 + 0.193411 -0.009694 + 0.206050 -0.008630 + 0.218742 -0.007529 + 0.231440 -0.006400 + 0.244158 -0.005241 + 0.256910 -0.004057 + 0.269681 -0.002850 + 0.282480 -0.001625 + 0.295305 -0.000384 + 0.308156 0.000868 + 0.321032 0.002128 + 0.333913 0.003392 + 0.346783 0.004654 + 0.359635 0.005909 + 0.372467 0.007153 + 0.385276 0.008384 + 0.398059 0.009597 + 0.410820 0.010790 + 0.423552 0.011959 + 0.436256 0.013099 + 0.448946 0.014210 + 0.461611 0.015287 + 0.474248 0.016327 + 0.486862 0.017326 + 0.499457 0.018282 + 0.512033 0.019193 + 0.524579 0.020054 + 0.537100 0.020862 + 0.549609 0.021615 + 0.562098 0.022310 + 0.574564 0.022944 + 0.587003 0.023515 + 0.599418 0.024018 + 0.611818 0.024452 + 0.624191 0.024814 + 0.636544 0.025100 + 0.648879 0.025309 + 0.661190 0.025437 + 0.673486 0.025484 + 0.685780 0.025446 + 0.698073 0.025326 + 0.710364 0.025122 + 0.722657 0.024835 + 0.734953 0.024465 + 0.747251 0.024014 + 0.759542 0.023481 + 0.771827 0.022866 + 0.784123 0.022167 + 0.796423 0.021390 + 0.808708 0.020532 + 0.820996 0.019594 + 0.833289 0.018576 + 0.845583 0.017480 + 0.857874 0.016307 + 0.870161 0.015057 + 0.882452 0.013730 + 0.894753 0.012327 + 0.907057 0.010852 + 0.919355 0.009305 + 0.931659 0.007687 + 0.943946 0.006002 + 0.956207 0.004255 + 0.968243 0.002479 + 0.979464 0.000770 + 0.989417 -0.000787 + 0.996606 -0.001935 + 1.000000 -0.002487 + +https://groups.yahoo.com/neo/groups/XFOIL/files/Free%20flite%20airfoils/ +This airfoil was develope from two my diffrente airfoils: +bottom side is from airfoil MID 103 and upper side is +from MID 106, both developed separately earlier. New +hybrid airfoil MID 104 has thickness of 7.74%, and camber +of 4.5%. It is intended for all free flite (FF) airplane models +for low speed with Re numbers from 40,000 and more. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid105.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid105.dat new file mode 100644 index 00000000..7ea3bbf0 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid105.dat @@ -0,0 +1,205 @@ +MID 105 7.5% class of P-30 rubber powered (c)Slobodan Midic + 1.000000 0.002542 + 0.996407 0.003026 + 0.988857 0.004077 + 0.978698 0.005550 + 0.967529 0.007237 + 0.955620 0.009102 + 0.943417 0.011060 + 0.931111 0.013049 + 0.918812 0.015021 + 0.906586 0.016948 + 0.894389 0.018826 + 0.882174 0.020661 + 0.869919 0.022460 + 0.857625 0.024230 + 0.845304 0.025972 + 0.832979 0.027685 + 0.820633 0.029372 + 0.808273 0.031035 + 0.795915 0.032671 + 0.783547 0.034282 + 0.771167 0.035870 + 0.758782 0.037434 + 0.746392 0.038974 + 0.733992 0.040493 + 0.721575 0.041991 + 0.709157 0.043470 + 0.696745 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-0,0 +1,263 @@ +MID 106 7.5% class of P-30 rubber powered (c)Slobodan Midic + 1.000000 0.002542 + 0.999804 0.002573 + 0.999295 0.002665 + 0.998454 0.002819 + 0.997288 0.003036 + 0.995801 0.003311 + 0.993995 0.003645 + 0.991873 0.004038 + 0.989440 0.004491 + 0.986700 0.005000 + 0.983656 0.005565 + 0.980308 0.006187 + 0.976665 0.006867 + 0.972730 0.007601 + 0.968505 0.008389 + 0.963995 0.009231 + 0.959206 0.010129 + 0.954144 0.011079 + 0.948811 0.012078 + 0.943210 0.013130 + 0.937351 0.014236 + 0.931242 0.015391 + 0.924886 0.016594 + 0.918288 0.017847 + 0.911462 0.019152 + 0.904421 0.020501 + 0.897171 0.021883 + 0.889716 0.023291 + 0.882058 0.024720 + 0.874199 0.026166 + 0.866139 0.027625 + 0.857883 0.029100 + 0.849438 0.030590 + 0.840809 0.032090 + 0.832002 0.033599 + 0.823022 0.035116 + 0.813878 0.036639 + 0.804575 0.038162 + 0.795117 0.039681 + 0.785511 0.041196 + 0.775764 0.042704 + 0.765881 0.044199 + 0.755864 0.045677 + 0.745720 0.047139 + 0.735455 0.048582 + 0.725073 0.049999 + 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0.000459 + 0.975532 -0.000022 + 0.979428 -0.000473 + 0.982990 -0.000894 + 0.986214 -0.001281 + 0.989102 -0.001632 + 0.991653 -0.001945 + 0.993867 -0.002221 + 0.995741 -0.002457 + 0.997277 -0.002651 + 0.998475 -0.002804 + 0.999335 -0.002916 + 0.999852 -0.002984 + 1.000000 -0.003007 + +https://groups.yahoo.com/neo/groups/XFOIL/files/Free%20flite%20airfoils/ +Airfoil MID 106 has thickness of 7.5%c, camber of 4.4%c, leadind edge radius of +0.55%c, and trailling edge gap of 0.5%c. It is similar to MID 105, only +differrence is a little more cambered top surface in last part of cord. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid107.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid107.dat new file mode 100644 index 00000000..f051d451 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid107.dat @@ -0,0 +1,230 @@ +MID 107 10% (c) Slobodan Midic low speed Re numbers from 40,000 and more + 1.000000 0.004891 + 0.996024 0.005585 + 0.988989 0.006862 + 0.980427 0.008486 + 0.970314 0.010500 + 0.958680 0.012926 + 0.945732 0.015709 + 0.932070 0.018658 + 0.918177 0.021594 + 0.904157 0.024469 + 0.890057 0.027271 + 0.875875 0.029996 + 0.861488 0.032684 + 0.847134 0.035310 + 0.832811 0.037840 + 0.818351 0.040330 + 0.804046 0.042720 + 0.789609 0.045043 + 0.775153 0.047311 + 0.760746 0.049488 + 0.746202 0.051614 + 0.731647 0.053684 + 0.717185 0.055667 + 0.702541 0.057599 + 0.687961 0.059481 + 0.673500 0.061259 + 0.658844 0.062997 + 0.644323 0.064661 + 0.629875 0.066232 + 0.615266 0.067742 + 0.600721 0.069196 + 0.586325 0.070542 + 0.571722 0.071828 + 0.557174 0.073054 + 0.542778 0.074182 + 0.528231 0.075228 + 0.513626 0.076228 + 0.499261 0.077127 + 0.484744 0.077939 + 0.470139 0.078696 + 0.455748 0.079371 + 0.441327 0.079938 + 0.426728 0.080454 + 0.412422 0.080884 + 0.398152 0.081203 + 0.383768 0.081438 + 0.369612 0.081593 + 0.355632 0.081614 + 0.341465 0.081534 + 0.327586 0.081360 + 0.313826 0.081042 + 0.299964 0.080601 + 0.286255 0.080051 + 0.272753 0.079361 + 0.259076 0.078517 + 0.245635 0.077576 + 0.232321 0.076462 + 0.218839 0.075208 + 0.205750 0.073845 + 0.192603 0.072291 + 0.179623 0.070630 + 0.166982 0.068816 + 0.154344 0.066827 + 0.142142 0.064731 + 0.130123 0.062441 + 0.118401 0.060041 + 0.107403 0.057564 + 0.096798 0.054924 + 0.086849 0.052230 + 0.077694 0.049464 + 0.069053 0.046559 + 0.060994 0.043599 + 0.053676 0.040666 + 0.047113 0.037799 + 0.041250 0.035019 + 0.036064 0.032398 + 0.031569 0.029996 + 0.027698 0.027787 + 0.024336 0.025736 + 0.021392 0.023839 + 0.018803 0.022091 + 0.016513 0.020482 + 0.014474 0.018997 + 0.012648 0.017626 + 0.011010 0.016351 + 0.009540 0.015148 + 0.008221 0.013996 + 0.007037 0.012882 + 0.005975 0.011797 + 0.005024 0.010735 + 0.004177 0.009691 + 0.003425 0.008662 + 0.002764 0.007647 + 0.002182 0.006647 + 0.001664 0.005669 + 0.001203 0.004715 + 0.000796 0.003782 + 0.000452 0.002864 + 0.000198 0.001957 + 0.000054 0.001064 + 0.000002 0.000187 + 0.000021 -0.000682 + 0.000114 -0.001562 + 0.000295 -0.002456 + 0.000575 -0.003352 + 0.000960 -0.004234 + 0.001453 -0.005097 + 0.002040 -0.005945 + 0.002712 -0.006780 + 0.003466 -0.007602 + 0.004307 -0.008408 + 0.005236 -0.009203 + 0.006252 -0.009991 + 0.007358 -0.010776 + 0.008560 -0.011560 + 0.009866 -0.012344 + 0.011289 -0.013125 + 0.012842 -0.013905 + 0.014542 -0.014683 + 0.016408 -0.015463 + 0.018464 -0.016246 + 0.020742 -0.017033 + 0.023281 -0.017826 + 0.026133 -0.018631 + 0.029360 -0.019455 + 0.033025 -0.020305 + 0.037202 -0.021162 + 0.042022 -0.021995 + 0.047682 -0.022821 + 0.054308 -0.023654 + 0.061927 -0.024437 + 0.070652 -0.025126 + 0.080637 -0.025704 + 0.091780 -0.026177 + 0.103593 -0.026506 + 0.116235 -0.026655 + 0.129440 -0.026705 + 0.142632 -0.026587 + 0.156482 -0.026317 + 0.170282 -0.025968 + 0.184193 -0.025460 + 0.198457 -0.024887 + 0.212541 -0.024223 + 0.227052 -0.023440 + 0.241529 -0.022614 + 0.255889 -0.021693 + 0.270513 -0.020672 + 0.285172 -0.019604 + 0.299585 -0.018473 + 0.314238 -0.017240 + 0.328904 -0.015981 + 0.343453 -0.014652 + 0.358213 -0.013235 + 0.373084 -0.011789 + 0.387796 -0.010322 + 0.402698 -0.008771 + 0.417856 -0.007190 + 0.432931 -0.005618 + 0.447819 -0.004032 + 0.462704 -0.002458 + 0.477802 -0.000901 + 0.492957 0.000661 + 0.507873 0.002191 + 0.522693 0.003648 + 0.537665 0.005076 + 0.552559 0.006471 + 0.567160 0.007780 + 0.581755 0.009001 + 0.596418 0.010172 + 0.610859 0.011265 + 0.625067 0.012239 + 0.639358 0.013113 + 0.653631 0.013908 + 0.667656 0.014594 + 0.681552 0.015141 + 0.695542 0.015573 + 0.709501 0.015899 + 0.723272 0.016099 + 0.737090 0.016153 + 0.751053 0.016098 + 0.764903 0.015932 + 0.778658 0.015632 + 0.792585 0.015195 + 0.806511 0.014660 + 0.820310 0.013998 + 0.834220 0.013204 + 0.848185 0.012298 + 0.862041 0.011285 + 0.875957 0.010136 + 0.889960 0.008879 + 0.903844 0.007518 + 0.917795 0.006036 + 0.931649 0.004476 + 0.945107 0.002867 + 0.957937 0.001232 + 0.969767 -0.000369 + 0.980158 -0.001853 + 0.988930 -0.003165 + 0.996071 -0.004267 + 1.000000 -0.004891 + +*modification tracfoil 0.999965->1.000000 0.004891 / 1.000035->1.000000 -0.004891 + +MID 107 10% +=========== + +This airfoil has thickness of 10%, and camber of 4%. +It is intended for all FF airplane models for low speed +with Re numbers from 40,000 and more. + +Airfoil must have appropriate turbulators at the top and/or +bootom side to provide turbulent flow on up side from +30%c and on down side from 5%c. By some models, they +fly only with higher lift, turbulator on the bottom side is +not need. To make turbulators more effective at small Re +numbers, on the top side invigators after 50%c are +welcome. + +Because of relative big thickness of 10% it is easy to +build models also with wing of high aspect ratio +to the conventional mode with wooden spars. + +Drag coeficient CD at zero lift CL=0 is very small in +comparison with usualy airfoils wit high cambers, so +the model can be suitable for succesfull vertical launching. + +Slobodan Midic + +Novi Sad, Jan. 2010. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid108a.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid108a.dat new file mode 100644 index 00000000..64b36d8a --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid108a.dat @@ -0,0 +1,206 @@ +MID 108a 8.5% for FF models (c)Slobodan Midic + 1.000000 0.004158 + 0.996024 0.004765 + 0.988989 0.005879 + 0.980427 0.007296 + 0.970314 0.009051 + 0.958680 0.011163 + 0.945732 0.013583 + 0.932070 0.016147 + 0.918177 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the thickness of 8.5%c but camber at +MID 108a is 3.5% and at MID 108b is 3.0%. LE radius +at MID 108a is 0.8%c, at MID 108b is 0.55%c. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid108b.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid108b.dat new file mode 100644 index 00000000..e1802687 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid108b.dat @@ -0,0 +1,206 @@ +MID 108b 8.5% for FF models (c)Slobodan Midic + 1.000000 0.004156 + 0.996388 0.004633 + 0.989207 0.005617 + 0.979791 0.006977 + 0.968765 0.008664 + 0.956935 0.010569 + 0.944610 0.012614 + 0.932140 0.014691 + 0.919750 0.016719 + 0.907374 0.018693 + 0.894984 0.020618 + 0.882592 0.022492 + 0.870129 0.024326 + 0.857585 0.026139 + 0.845120 0.027908 + 0.832648 0.029625 + 0.820095 0.031321 + 0.807622 0.032969 + 0.795134 0.034569 + 0.782579 0.036142 + 0.770062 0.037674 + 0.757535 0.039162 + 0.744946 0.040623 + 0.732366 0.042053 + 0.719837 0.043438 + 0.707237 0.044788 + 0.694596 0.046122 + 0.682068 0.047407 + 0.669498 0.048650 + 0.656867 0.049870 + 0.644304 0.051052 + 0.631793 0.052182 + 0.619202 0.053272 + 0.606580 0.054339 + 0.594073 0.055355 + 0.581547 0.056318 + 0.568924 0.057250 + 0.556347 0.058149 + 0.543870 0.058988 + 0.531310 0.059777 + 0.518683 0.060541 + 0.506166 0.061256 + 0.493664 0.061914 + 0.481083 0.062527 + 0.468480 0.063107 + 0.455993 0.063637 + 0.443492 0.064102 + 0.430869 0.064533 + 0.418353 0.064922 + 0.405922 0.065247 + 0.393440 0.065507 + 0.380909 0.065724 + 0.368541 0.065883 + 0.356211 0.065955 + 0.343756 0.065965 + 0.331427 0.065916 + 0.319201 0.065777 + 0.306894 0.065553 + 0.294599 0.065256 + 0.282418 0.064879 + 0.270267 0.064399 + 0.258014 0.063828 + 0.245901 0.063185 + 0.233872 0.062424 + 0.221664 0.061563 + 0.209667 0.060629 + 0.197715 0.059567 + 0.185672 0.058403 + 0.173868 0.057146 + 0.162081 0.055753 + 0.150344 0.054245 + 0.138815 0.052615 + 0.127288 0.050830 + 0.115970 0.048935 + 0.105018 0.046906 + 0.094250 0.044703 + 0.083953 0.042377 + 0.074137 0.039865 + 0.064565 0.037114 + 0.055439 0.034188 + 0.046881 0.031098 + 0.038842 0.027835 + 0.031576 0.024579 + 0.025370 0.021528 + 0.020187 0.018748 + 0.016062 0.016317 + 0.012865 0.014264 + 0.010390 0.012541 + 0.008435 0.011055 + 0.006849 0.009737 + 0.005532 0.008546 + 0.004429 0.007456 + 0.003498 0.006448 + 0.002704 0.005505 + 0.002023 0.004618 + 0.001440 0.003773 + 0.000943 0.002967 + 0.000526 0.002195 + 0.000213 0.001439 + 0.000045 0.000687 + 0.000000 -0.000042 + 0.000054 -0.000771 + 0.000217 -0.001521 + 0.000507 -0.002271 + 0.000930 -0.003011 + 0.001485 -0.003732 + 0.002155 -0.004450 + 0.002936 -0.005177 + 0.003840 -0.005920 + 0.004885 -0.006688 + 0.006093 -0.007493 + 0.007497 -0.008351 + 0.009144 -0.009273 + 0.011101 -0.010274 + 0.013462 -0.011358 + 0.016356 -0.012543 + 0.019948 -0.013836 + 0.024446 -0.015230 + 0.030077 -0.016712 + 0.036829 -0.018197 + 0.044727 -0.019560 + 0.053771 -0.020791 + 0.063570 -0.021833 + 0.074012 -0.022657 + 0.085109 -0.023306 + 0.096577 -0.023809 + 0.108182 -0.024155 + 0.120203 -0.024372 + 0.132247 -0.024506 + 0.144245 -0.024512 + 0.156586 -0.024421 + 0.168825 -0.024271 + 0.181107 -0.024016 + 0.193632 -0.023699 + 0.206039 -0.023338 + 0.218439 -0.022898 + 0.231042 -0.022400 + 0.243517 -0.021873 + 0.255938 -0.021276 + 0.268506 -0.020618 + 0.281095 -0.019924 + 0.293586 -0.019190 + 0.306093 -0.018395 + 0.318762 -0.017552 + 0.331325 -0.016693 + 0.343827 -0.015780 + 0.356486 -0.014812 + 0.369223 -0.013823 + 0.381865 -0.012820 + 0.394458 -0.011780 + 0.407146 -0.010704 + 0.419923 -0.009624 + 0.432658 -0.008538 + 0.445403 -0.007430 + 0.458145 -0.006321 + 0.470887 -0.005231 + 0.483664 -0.004147 + 0.496454 -0.003056 + 0.509140 -0.001981 + 0.521792 -0.000943 + 0.534522 0.000076 + 0.547272 0.001083 + 0.559907 0.002062 + 0.572446 0.002988 + 0.585057 0.003874 + 0.597713 0.004736 + 0.610240 0.005556 + 0.622663 0.006309 + 0.635130 0.007000 + 0.647658 0.007646 + 0.660104 0.008241 + 0.672427 0.008760 + 0.684768 0.009198 + 0.697155 0.009571 + 0.709529 0.009878 + 0.721801 0.010109 + 0.734083 0.010248 + 0.746470 0.010316 + 0.758835 0.010321 + 0.771119 0.010249 + 0.783410 0.010090 + 0.795805 0.009857 + 0.808159 0.009563 + 0.820450 0.009189 + 0.832797 0.008735 + 0.845187 0.008213 + 0.857529 0.007628 + 0.869844 0.006965 + 0.882233 0.006226 + 0.894616 0.005427 + 0.906967 0.004559 + 0.919390 0.003619 + 0.931819 0.002628 + 0.944153 0.001583 + 0.956356 0.000479 + 0.968292 -0.000678 + 0.979537 -0.001843 + 0.989165 -0.002902 + 0.996444 -0.003736 + 1.000000 -0.004156 + +https://groups.yahoo.com/neo/groups/XFOIL/files/Free%20flite%20airfoils/ +Both airfoils are with the thickness of 8.5%c but camber at +MID 108a is 3.5% and at MID 108b is 3.0%. LE radius +at MID 108a is 0.8%c, at MID 108b is 0.55%c. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid110.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid110.dat new file mode 100644 index 00000000..3f6c0740 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid110.dat @@ -0,0 +1,161 @@ +MID 110 (c)Slobodan Midic F1A models Re~40k Tri + 1.000000 0.004466 + 0.994701 0.006186 + 0.984173 0.009520 + 0.971428 0.013402 + 0.958151 0.017262 + 0.944378 0.021078 + 0.930359 0.024779 + 0.916307 0.028311 + 0.902218 0.031671 + 0.888064 0.034865 + 0.873819 0.037906 + 0.859467 0.040810 + 0.845026 0.043589 + 0.830521 0.046247 + 0.815944 0.048793 + 0.801278 0.051243 + 0.786522 0.053613 + 0.771718 0.055909 + 0.756890 0.058129 + 0.742021 0.060281 + 0.727124 0.062369 + 0.712221 0.064389 + 0.697288 0.066347 + 0.682315 0.068250 + 0.667327 0.070101 + 0.652341 0.071896 + 0.637349 0.073634 + 0.622333 0.075320 + 0.607314 0.076955 + 0.592323 0.078530 + 0.577321 0.080044 + 0.562295 0.081503 + 0.547299 0.082903 + 0.532316 0.084233 + 0.517311 0.085501 + 0.502328 0.086702 + 0.487376 0.087826 + 0.472404 0.088875 + 0.457436 0.089851 + 0.442507 0.090745 + 0.427579 0.091551 + 0.412650 0.092273 + 0.397758 0.092903 + 0.382914 0.093432 + 0.368112 0.093849 + 0.353345 0.094146 + 0.338632 0.094316 + 0.323976 0.094345 + 0.309332 0.094226 + 0.294695 0.093962 + 0.280104 0.093547 + 0.265545 0.092973 + 0.251011 0.092239 + 0.236566 0.091341 + 0.222260 0.090261 + 0.208097 0.088977 + 0.194066 0.087466 + 0.180157 0.085712 + 0.166372 0.083701 + 0.152728 0.081423 + 0.139275 0.078869 + 0.126098 0.076033 + 0.113249 0.072889 + 0.100752 0.069408 + 0.088641 0.065570 + 0.076919 0.061351 + 0.065609 0.056740 + 0.054958 0.051827 + 0.045122 0.046638 + 0.036022 0.041121 + 0.027944 0.035528 + 0.021216 0.030102 + 0.015748 0.024898 + 0.011383 0.020076 + 0.008001 0.015891 + 0.005479 0.012461 + 0.003642 0.009586 + 0.002265 0.007110 + 0.001217 0.004951 + 0.000497 0.003028 + 0.000096 0.001284 + -0.000003 -0.000364 + 0.000245 -0.001968 + 0.000922 -0.003488 + 0.002098 -0.004747 + 0.003778 -0.005653 + 0.005846 -0.006257 + 0.008318 -0.006596 + 0.011342 -0.006720 + 0.015182 -0.006671 + 0.020214 -0.006426 + 0.027038 -0.005858 + 0.036308 -0.004842 + 0.047612 -0.003313 + 0.060125 -0.001252 + 0.073700 0.001283 + 0.087845 0.004132 + 0.102303 0.007187 + 0.117005 0.010367 + 0.131590 0.013507 + 0.145910 0.016475 + 0.160111 0.019245 + 0.174349 0.021829 + 0.188708 0.024256 + 0.203191 0.026548 + 0.217769 0.028718 + 0.232407 0.030774 + 0.247080 0.032717 + 0.261775 0.034547 + 0.276493 0.036266 + 0.291238 0.037876 + 0.305995 0.039378 + 0.320742 0.040768 + 0.335499 0.042043 + 0.350293 0.043209 + 0.365067 0.044265 + 0.379813 0.045200 + 0.394616 0.046018 + 0.409442 0.046733 + 0.424229 0.047333 + 0.439058 0.047817 + 0.453960 0.048205 + 0.468864 0.048499 + 0.483773 0.048697 + 0.498721 0.048807 + 0.513695 0.048834 + 0.528615 0.048778 + 0.543452 0.048622 + 0.558346 0.048354 + 0.573341 0.048002 + 0.588282 0.047575 + 0.603174 0.047054 + 0.618111 0.046441 + 0.633064 0.045745 + 0.647976 0.044965 + 0.662844 0.044095 + 0.677728 0.043126 + 0.692631 0.042067 + 0.707455 0.040922 + 0.722237 0.039669 + 0.737067 0.038307 + 0.751860 0.036854 + 0.766580 0.035295 + 0.781325 0.033618 + 0.796062 0.031838 + 0.810722 0.029952 + 0.825370 0.027943 + 0.840043 0.025816 + 0.854707 0.023578 + 0.869366 0.021231 + 0.884039 0.018777 + 0.898726 0.016222 + 0.913380 0.013578 + 0.927982 0.010845 + 0.942575 0.008009 + 0.956925 0.005119 + 0.970689 0.002228 + 0.983809 -0.000668 + 0.994583 -0.003166 + 1.000000 -0.004466 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid111.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid111.dat new file mode 100644 index 00000000..fcf3bca6 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid111.dat @@ -0,0 +1,161 @@ +MID 111 (c)Slobodan Midic F1H,A Re40-60k tt30% t + 1.000000 0.005951 + 0.994578 0.007355 + 0.984213 0.010018 + 0.971528 0.013222 + 0.957653 0.016638 + 0.943017 0.020142 + 0.928060 0.023622 + 0.913018 0.027016 + 0.897907 0.030319 + 0.882764 0.033525 + 0.867613 0.036624 + 0.852443 0.039618 + 0.837258 0.042506 + 0.822071 0.045282 + 0.806874 0.047946 + 0.791652 0.050498 + 0.776388 0.052944 + 0.761052 0.055293 + 0.745625 0.057561 + 0.730118 0.059757 + 0.714536 0.061889 + 0.698875 0.063970 + 0.683140 0.066010 + 0.667379 0.068012 + 0.651661 0.069965 + 0.635963 0.071859 + 0.620235 0.073703 + 0.604539 0.075493 + 0.588898 0.077211 + 0.573236 0.078862 + 0.557544 0.080455 + 0.541864 0.081985 + 0.526176 0.083449 + 0.510472 0.084854 + 0.494783 0.086197 + 0.479130 0.087470 + 0.463548 0.088665 + 0.448109 0.089760 + 0.432821 0.090726 + 0.417635 0.091547 + 0.402552 0.092212 + 0.387575 0.092700 + 0.372642 0.093003 + 0.357660 0.093120 + 0.342567 0.093068 + 0.327426 0.092865 + 0.312297 0.092509 + 0.297153 0.092000 + 0.282023 0.091345 + 0.266978 0.090537 + 0.252033 0.089566 + 0.237170 0.088420 + 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b/aerosandbox/geometry/airfoil/airfoil_database/mid117.dat new file mode 100644 index 00000000..16367602 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid117.dat @@ -0,0 +1,143 @@ +MID 117 for F1A (c) slobodan.midic + 1.000000 0.006013 + 0.993274 0.007566 + 0.980278 0.010520 + 0.964893 0.013930 + 0.948669 0.017424 + 0.932237 0.020852 + 0.915752 0.024173 + 0.899251 0.027379 + 0.882745 0.030462 + 0.866227 0.033415 + 0.849699 0.036243 + 0.833164 0.038931 + 0.816592 0.041491 + 0.799979 0.043922 + 0.783276 0.046247 + 0.766512 0.048483 + 0.749699 0.050636 + 0.732863 0.052714 + 0.716013 0.054711 + 0.699144 0.056633 + 0.682276 0.058477 + 0.665392 0.060244 + 0.648510 0.061933 + 0.631626 0.063539 + 0.614730 0.065067 + 0.597846 0.066511 + 0.580953 0.067868 + 0.564053 0.069144 + 0.547163 0.070330 + 0.530257 0.071428 + 0.513350 0.072443 + 0.496447 0.073365 + 0.479525 0.074202 + 0.462615 0.074952 + 0.445707 0.075607 + 0.428788 0.076175 + 0.411903 0.076652 + 0.395053 0.077021 + 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0.004389 + 0.980168 0.001817 + 0.993295 -0.000464 + 1.000000 -0.001659 + +https://groups.yahoo.com/neo/groups/XFOIL/files/Free%20flite%20airfoils/ \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid118.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid118.dat new file mode 100644 index 00000000..88730f38 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid118.dat @@ -0,0 +1,149 @@ +MID 118 Airfoil for F1B and F1A (c)Slobodan Midic + 1.000000 0.008410 + 0.993661 0.010196 + 0.980504 0.013789 + 0.965121 0.017814 + 0.949265 0.021765 + 0.933309 0.025542 + 0.917305 0.029135 + 0.901263 0.032551 + 0.885139 0.035804 + 0.868922 0.038927 + 0.852620 0.041944 + 0.836256 0.044866 + 0.819845 0.047709 + 0.803398 0.050474 + 0.786922 0.053171 + 0.770434 0.055801 + 0.753930 0.058370 + 0.737434 0.060874 + 0.720933 0.063312 + 0.704439 0.065683 + 0.687955 0.067979 + 0.671470 0.070197 + 0.654997 0.072331 + 0.638523 0.074371 + 0.622043 0.076319 + 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-0.005729 + 0.006132 -0.006710 + 0.008798 -0.007548 + 0.011989 -0.008330 + 0.016075 -0.009060 + 0.021499 -0.009662 + 0.029043 -0.010041 + 0.040428 -0.009843 + 0.055303 -0.008947 + 0.071016 -0.007947 + 0.085272 -0.006875 + 0.099587 -0.005419 + 0.116971 -0.003085 + 0.140855 0.000735 + 0.167800 0.005193 + 0.187312 0.008410 + 0.192501 0.009291 + 0.199750 0.010535 + 0.216341 0.013423 + 0.242497 0.018005 + 0.267746 0.022329 + 0.287255 0.025561 + 0.302888 0.028109 + 0.316800 0.030361 + 0.331188 0.032691 + 0.347018 0.035275 + 0.363826 0.037954 + 0.381061 0.040506 + 0.398201 0.042825 + 0.414894 0.044853 + 0.431208 0.046638 + 0.447291 0.048242 + 0.463340 0.049725 + 0.479595 0.051139 + 0.496303 0.052379 + 0.513310 0.053328 + 0.530246 0.054045 + 0.547091 0.054475 + 0.563848 0.054564 + 0.580511 0.054355 + 0.597095 0.053915 + 0.613689 0.053231 + 0.630385 0.052315 + 0.647226 0.051195 + 0.664234 0.049904 + 0.681394 0.048482 + 0.698696 0.046964 + 0.716040 0.045388 + 0.733287 0.043757 + 0.750404 0.042046 + 0.767394 0.040226 + 0.784259 0.038275 + 0.801008 0.036169 + 0.817707 0.033880 + 0.834436 0.031405 + 0.851192 0.028758 + 0.867985 0.025947 + 0.884821 0.022986 + 0.901649 0.019896 + 0.918351 0.016692 + 0.934806 0.013361 + 0.950962 0.009865 + 0.966695 0.006210 + 0.981369 0.002562 + 0.993771 -0.000697 + 1.000000 -0.002399 + +https://groups.yahoo.com/neo/groups/XFOIL/files/Free%20flite%20airfoils/ +Airfoil Mid 118 was basicaly designed for F1B class of rubber +powered flying model to FAI propositions, and in this application +wing with this airfoil need to have only upper turbulator as a +trip-top on 30% of cord. +Thickness of Mid 118 airfoil is 7.5%c, camber is 6.8%c, LE radius +is 0.85%c \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid120.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid120.dat new file mode 100644 index 00000000..62da1dd8 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid120.dat @@ -0,0 +1,161 @@ +MID 120 (c)Slobodan Midic F1G,K + 1.000000 0.005310 + 0.994609 0.006327 + 0.983622 0.008379 + 0.969792 0.010916 + 0.955836 0.013415 + 0.942166 0.015798 + 0.928181 0.018171 + 0.913977 0.020515 + 0.899827 0.022785 + 0.885719 0.024983 + 0.871585 0.027120 + 0.857428 0.029194 + 0.843270 0.031201 + 0.829116 0.033140 + 0.814960 0.035008 + 0.800796 0.036804 + 0.786617 0.038532 + 0.772418 0.040192 + 0.758192 0.041791 + 0.743934 0.043335 + 0.729641 0.044832 + 0.715317 0.046288 + 0.700967 0.047711 + 0.686597 0.049105 + 0.672216 0.050473 + 0.657832 0.051814 + 0.643452 0.053128 + 0.629080 0.054412 + 0.614714 0.055663 + 0.600355 0.056879 + 0.585999 0.058058 + 0.571641 0.059199 + 0.557278 0.060302 + 0.542912 0.061368 + 0.528547 0.062397 + 0.514177 0.063388 + 0.499801 0.064341 + 0.485428 0.065258 + 0.471074 0.066132 + 0.456762 0.066953 + 0.442504 0.067708 + 0.428288 0.068383 + 0.414100 0.068968 + 0.399959 0.069453 + 0.385871 0.069823 + 0.371793 0.070070 + 0.357669 0.070198 + 0.343507 0.070222 + 0.329340 0.070143 + 0.315171 0.069964 + 0.300986 0.069686 + 0.286801 0.069314 + 0.272648 0.068844 + 0.258531 0.068268 + 0.244439 0.067580 + 0.230382 0.066775 + 0.216379 0.065843 + 0.202444 0.064773 + 0.188583 0.063550 + 0.174810 0.062161 + 0.161147 0.060587 + 0.147610 0.058809 + 0.134212 0.056806 + 0.120962 0.054558 + 0.107909 0.052036 + 0.095210 0.049232 + 0.082986 0.046120 + 0.071057 0.042589 + 0.059169 0.038547 + 0.047615 0.034132 + 0.036992 0.029547 + 0.027360 0.024766 + 0.019006 0.019961 + 0.012743 0.015817 + 0.008413 0.012461 + 0.005420 0.009691 + 0.003307 0.007331 + 0.001811 0.005279 + 0.000804 0.003439 + 0.000215 0.001726 + 0.000012 0.000119 + 0.000215 -0.001412 + 0.000860 -0.002901 + 0.001993 -0.004280 + 0.003666 -0.005438 + 0.005879 -0.006336 + 0.008735 -0.006964 + 0.012674 -0.007385 + 0.018312 -0.007686 + 0.025766 -0.007632 + 0.035125 -0.006973 + 0.046837 -0.005617 + 0.060337 -0.003728 + 0.074207 -0.001612 + 0.087963 0.000502 + 0.101698 0.002499 + 0.115575 0.004389 + 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--- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid31_F3J_F5J.dat @@ -0,0 +1,141 @@ +MID-31 F3J F5J (C)Slobodan Midic + 1.000000 -0.000065 + 0.993215 0.000862 + 0.979358 0.002893 + 0.963716 0.005225 + 0.947840 0.007613 + 0.931944 0.009993 + 0.916054 0.012339 + 0.900162 0.014657 + 0.884262 0.016942 + 0.868363 0.019198 + 0.852458 0.021419 + 0.836547 0.023613 + 0.820650 0.025767 + 0.804742 0.027885 + 0.788838 0.029964 + 0.772932 0.032001 + 0.757038 0.033992 + 0.741135 0.035930 + 0.725214 0.037828 + 0.709311 0.039676 + 0.693403 0.041469 + 0.677486 0.043211 + 0.661582 0.044895 + 0.645671 0.046518 + 0.629757 0.048082 + 0.613848 0.049581 + 0.597928 0.051016 + 0.582008 0.052386 + 0.566088 0.053688 + 0.550161 0.054922 + 0.534244 0.056085 + 0.518328 0.057170 + 0.502396 0.058182 + 0.486474 0.059119 + 0.470556 0.059974 + 0.454627 0.060749 + 0.438714 0.061442 + 0.422806 0.062042 + 0.406891 0.062553 + 0.390993 0.062971 + 0.375099 0.063288 + 0.359204 0.063506 + 0.343338 0.063618 + 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--git a/aerosandbox/geometry/airfoil/airfoil_database/mid321a.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid321a.dat new file mode 100644 index 00000000..7576eae5 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid321a.dat @@ -0,0 +1,148 @@ +MID 321a 9% #SloMi-Near flat bottom-Electro RC fly (c)Slobodan Midic + 1.000000 0.001454 + 0.993441 0.002266 + 0.980367 0.004225 + 0.965488 0.006779 + 0.949816 0.009672 + 0.933831 0.012673 + 0.917882 0.015627 + 0.901942 0.018499 + 0.886015 0.021289 + 0.870099 0.023977 + 0.854151 0.026572 + 0.838140 0.029087 + 0.822025 0.031561 + 0.805884 0.034008 + 0.789760 0.036415 + 0.773638 0.038778 + 0.757515 0.041095 + 0.741366 0.043370 + 0.725210 0.045610 + 0.709086 0.047802 + 0.692983 0.049930 + 0.676841 0.052002 + 0.660678 0.054033 + 0.644566 0.056004 + 0.628477 0.057895 + 0.612365 0.059713 + 0.596272 0.061455 + 0.580212 0.063100 + 0.564120 0.064650 + 0.547998 0.066120 + 0.531862 0.067510 + 0.515721 0.068823 + 0.499613 0.070048 + 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All three are intended as the airfoils for R/C +electric flying models, especially for Re numbers from 60,000 up to +400,000 and more. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid321b.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid321b.dat new file mode 100644 index 00000000..cf5e1fa9 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid321b.dat @@ -0,0 +1,148 @@ +MID 321b #SloMi-Near flat bottom 9.45%-Electro R/C (c)Slobodan Midic + 1.000000 0.001527 + 0.993466 0.002376 + 0.980634 0.004391 + 0.965840 0.007052 + 0.950111 0.010098 + 0.933987 0.013276 + 0.917882 0.016408 + 0.901786 0.019453 + 0.885703 0.022410 + 0.869635 0.025257 + 0.853530 0.028005 + 0.837345 0.030671 + 0.821047 0.033296 + 0.804721 0.035892 + 0.788413 0.038445 + 0.772105 0.040950 + 0.755797 0.043406 + 0.739461 0.045818 + 0.723118 0.048192 + 0.706817 0.050511 + 0.690533 0.052760 + 0.674199 0.054954 + 0.657856 0.057102 + 0.641576 0.059180 + 0.625308 0.061171 + 0.609019 0.063086 + 0.592765 0.064914 + 0.576536 0.066635 + 0.560259 0.068260 + 0.543959 0.069799 + 0.527642 0.071254 + 0.511330 0.072624 + 0.495061 0.073895 + 0.478780 0.075057 + 0.462477 0.076122 + 0.446197 0.077086 + 0.429969 0.077930 + 0.413767 0.078637 + 0.397536 0.079211 + 0.381300 0.079662 + 0.365129 0.079973 + 0.348990 0.080124 + 0.332823 0.080119 + 0.316672 0.079965 + 0.300600 0.079644 + 0.284559 0.079136 + 0.268526 0.078440 + 0.252528 0.077556 + 0.236580 0.076473 + 0.220693 0.075182 + 0.204895 0.073667 + 0.189175 0.071910 + 0.173570 0.069898 + 0.158092 0.067606 + 0.142749 0.065014 + 0.127583 0.062103 + 0.112633 0.058847 + 0.097941 0.055219 + 0.083604 0.051194 + 0.069692 0.046735 + 0.056371 0.041830 + 0.043803 0.036475 + 0.032438 0.030812 + 0.022799 0.025085 + 0.015249 0.019709 + 0.009925 0.015147 + 0.006291 0.011379 + 0.003787 0.008310 + 0.002048 0.005766 + 0.000877 0.003568 + 0.000198 0.001599 + 0.000005 -0.000216 + 0.000372 -0.001976 + 0.001442 -0.003677 + 0.003199 -0.005198 + 0.005637 -0.006613 + 0.008922 -0.008020 + 0.013478 -0.009495 + 0.020049 -0.011097 + 0.029491 -0.012793 + 0.041859 -0.014377 + 0.056148 -0.015654 + 0.071363 -0.016593 + 0.086994 -0.017228 + 0.102931 -0.017621 + 0.119045 -0.017834 + 0.135281 -0.017904 + 0.151587 -0.017857 + 0.167971 -0.017715 + 0.184386 -0.017495 + 0.200868 -0.017210 + 0.217384 -0.016882 + 0.233927 -0.016516 + 0.250499 -0.016125 + 0.267077 -0.015712 + 0.283693 -0.015284 + 0.300314 -0.014859 + 0.316922 -0.014432 + 0.333503 -0.013993 + 0.350064 -0.013530 + 0.366636 -0.013041 + 0.383227 -0.012535 + 0.399825 -0.012014 + 0.416439 -0.011484 + 0.433047 -0.010955 + 0.449638 -0.010440 + 0.466257 -0.009933 + 0.482879 -0.009422 + 0.499503 -0.008911 + 0.516131 -0.008403 + 0.532762 -0.007897 + 0.549386 -0.007393 + 0.565995 -0.006887 + 0.582589 -0.006389 + 0.599174 -0.005906 + 0.615747 -0.005444 + 0.632317 -0.005004 + 0.648903 -0.004587 + 0.665523 -0.004177 + 0.682128 -0.003775 + 0.698707 -0.003387 + 0.715256 -0.003026 + 0.731802 -0.002699 + 0.748387 -0.002397 + 0.764978 -0.002108 + 0.781543 -0.001840 + 0.798099 -0.001601 + 0.814650 -0.001389 + 0.831194 -0.001210 + 0.847736 -0.001062 + 0.864253 -0.000952 + 0.880763 -0.000885 + 0.897288 -0.000862 + 0.913833 -0.000874 + 0.930403 -0.000914 + 0.946949 -0.000972 + 0.963391 -0.001045 + 0.979144 -0.001092 + 0.993071 -0.001095 + 1.000000 -0.001092 + +MID 321a,b,c are 3 airfoils with near flat bottom. + +MID 321a has thickness of 9.0%, MID 321b is 9.45%, and +MID 321c is 10.0%. All three are intended as the airfoils for R/C +electric flying models, especially for Re numbers from 60,000 up to +400,000 and more. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid321c.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid321c.dat new file mode 100644 index 00000000..5c06a8f1 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid321c.dat @@ -0,0 +1,148 @@ +mid 321c #SloMi-Near flat bottom 10%-Electro R/C (c)Slobodan Midic + 1.000000 0.001615 + 0.993448 0.002517 + 0.980848 0.004607 + 0.966175 0.007395 + 0.950412 0.010621 + 0.934142 0.014015 + 0.917865 0.017365 + 0.901593 0.020621 + 0.885338 0.023782 + 0.869096 0.026823 + 0.852810 0.029759 + 0.836428 0.032610 + 0.819918 0.035421 + 0.803381 0.038201 + 0.786862 0.040933 + 0.770343 0.043613 + 0.753822 0.046239 + 0.737267 0.048819 + 0.720716 0.051357 + 0.704212 0.053831 + 0.687716 0.056230 + 0.671161 0.058573 + 0.654619 0.060863 + 0.638146 0.063069 + 0.621672 0.065184 + 0.605186 0.067216 + 0.588750 0.069146 + 0.572321 0.070961 + 0.555834 0.072677 + 0.539329 0.074300 + 0.522806 0.075833 + 0.506307 0.077271 + 0.489847 0.078593 + 0.473358 0.079803 + 0.456861 0.080908 + 0.440408 0.081898 + 0.424013 0.082750 + 0.407622 0.083452 + 0.391199 0.084015 + 0.374805 0.084441 + 0.358487 0.084706 + 0.342170 0.084796 + 0.325830 0.084722 + 0.309552 0.084484 + 0.293351 0.084053 + 0.277165 0.083418 + 0.261001 0.082583 + 0.244891 0.081540 + 0.228842 0.080279 + 0.212884 0.078790 + 0.197023 0.077050 + 0.181270 0.075047 + 0.165664 0.072761 + 0.150204 0.070168 + 0.134921 0.067250 + 0.119866 0.063987 + 0.105073 0.060350 + 0.090627 0.056324 + 0.076611 0.051875 + 0.063152 0.046995 + 0.050417 0.041680 + 0.038684 0.036018 + 0.028462 0.030237 + 0.020087 0.024612 + 0.013726 0.019567 + 0.009209 0.015295 + 0.006017 0.011709 + 0.003733 0.008716 + 0.002092 0.006178 + 0.000951 0.003951 + 0.000255 0.001939 + 0.000001 0.000080 + 0.000244 -0.001710 + 0.001117 -0.003471 + 0.002651 -0.005076 + 0.004795 -0.006533 + 0.007606 -0.007939 + 0.011308 -0.009356 + 0.016338 -0.010845 + 0.023371 -0.012441 + 0.033097 -0.014089 + 0.045532 -0.015608 + 0.059854 -0.016841 + 0.075144 -0.017749 + 0.090915 -0.018352 + 0.107035 -0.018719 + 0.123342 -0.018903 + 0.139787 -0.018942 + 0.156315 -0.018860 + 0.172926 -0.018682 + 0.189580 -0.018422 + 0.206314 -0.018100 + 0.223077 -0.017733 + 0.239879 -0.017330 + 0.256704 -0.016901 + 0.273548 -0.016449 + 0.290431 -0.015990 + 0.307306 -0.015533 + 0.324159 -0.015070 + 0.340980 -0.014588 + 0.357794 -0.014078 + 0.374629 -0.013543 + 0.391478 -0.012991 + 0.408341 -0.012425 + 0.425216 -0.011855 + 0.442066 -0.011293 + 0.458931 -0.010747 + 0.475814 -0.010199 + 0.492698 -0.009649 + 0.509585 -0.009102 + 0.526478 -0.008558 + 0.543367 -0.008015 + 0.560242 -0.007472 + 0.577096 -0.006933 + 0.593940 -0.006409 + 0.610766 -0.005905 + 0.627589 -0.005425 + 0.644418 -0.004971 + 0.661292 -0.004530 + 0.678159 -0.004095 + 0.694998 -0.003674 + 0.711802 -0.003279 + 0.728590 -0.002921 + 0.745419 -0.002592 + 0.762266 -0.002280 + 0.779086 -0.001987 + 0.795889 -0.001726 + 0.812688 -0.001494 + 0.829476 -0.001299 + 0.846264 -0.001136 + 0.863022 -0.001014 + 0.879771 -0.000940 + 0.896536 -0.000913 + 0.913325 -0.000924 + 0.930138 -0.000966 + 0.946915 -0.001029 + 0.963521 -0.001107 + 0.979297 -0.001156 + 0.993038 -0.001159 + 1.000000 -0.001155 + +MID 321a,b,c are 3 airfoils with near flat bottom. + +MID 321a has thickness of 9.0%, MID 321b is 9.45%, and +MID 321c is 10.0%. All three are intended as the airfoils for R/C +electric flying models, especially for Re numbers from 60,000 up to +400,000 and more. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid321d.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid321d.dat new file mode 100644 index 00000000..4557d7b1 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid321d.dat @@ -0,0 +1,141 @@ +mid 321d (c)Slobodan Midic small to medium wind turbine + 1.000000 0.002308 + 0.993448 0.003436 + 0.980848 0.006049 + 0.966175 0.009524 + 0.950411 0.013539 + 0.934141 0.017765 + 0.917864 0.021941 + 0.901592 0.026007 + 0.885337 0.029962 + 0.869094 0.033777 + 0.852808 0.037473 + 0.836426 0.041073 + 0.819916 0.044632 + 0.803379 0.048160 + 0.786860 0.051637 + 0.770340 0.055055 + 0.753819 0.058413 + 0.737264 0.061717 + 0.720713 0.064973 + 0.704209 0.068158 + 0.687713 0.071258 + 0.671157 0.074292 + 0.654615 0.077262 + 0.638142 0.080128 + 0.621668 0.082885 + 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+ 0.004796 -0.010708 + 0.007607 -0.013316 + 0.011309 -0.016040 + 0.016340 -0.018995 + 0.023373 -0.022287 + 0.033100 -0.025860 + 0.045535 -0.029371 + 0.059857 -0.032479 + 0.075148 -0.035036 + 0.090919 -0.037049 + 0.107039 -0.038621 + 0.123347 -0.039831 + 0.139792 -0.040741 + 0.156320 -0.041393 + 0.172931 -0.041829 + 0.189585 -0.042073 + 0.206319 -0.042161 + 0.223082 -0.042119 + 0.239884 -0.041966 + 0.256710 -0.041718 + 0.273554 -0.041384 + 0.290437 -0.040987 + 0.307312 -0.040536 + 0.324165 -0.040025 + 0.340986 -0.039445 + 0.357800 -0.038787 + 0.374634 -0.038051 + 0.391483 -0.037251 + 0.408346 -0.036398 + 0.425221 -0.035503 + 0.442071 -0.034578 + 0.458936 -0.033638 + 0.475819 -0.032666 + 0.492703 -0.031665 + 0.509590 -0.030636 + 0.526483 -0.029582 + 0.543372 -0.028506 + 0.560246 -0.027406 + 0.577100 -0.026287 + 0.593944 -0.025157 + 0.610770 -0.024024 + 0.627593 -0.022898 + 0.644422 -0.021782 + 0.661296 -0.020657 + 0.678162 -0.019523 + 0.695001 -0.018394 + 0.711805 -0.017281 + 0.728593 -0.016196 + 0.745422 -0.015135 + 0.762269 -0.014082 + 0.779088 -0.013039 + 0.795891 -0.012024 + 0.812690 -0.011032 + 0.829478 -0.010078 + 0.846266 -0.009151 + 0.863024 -0.008254 + 0.879772 -0.007388 + 0.896537 -0.006548 + 0.913326 -0.005728 + 0.930139 -0.004921 + 0.946916 -0.004125 + 0.963521 -0.003366 + 0.979297 -0.002668 + 0.993038 -0.002094 + 1.000000 -0.001853 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid321e.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid321e.dat new file mode 100644 index 00000000..7227d7a0 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid321e.dat @@ -0,0 +1,141 @@ +MID 321e (c)Slobodan Midic small to medium wind turbine + 1.000000 0.002311 + 0.993448 0.003623 + 0.980848 0.006664 + 0.966175 0.010718 + 0.950411 0.015408 + 0.934140 0.020341 + 0.917863 0.025212 + 0.901591 0.029948 + 0.885336 0.034547 + 0.869093 0.038973 + 0.852807 0.043249 + 0.836425 0.047403 + 0.819914 0.051501 + 0.803377 0.055555 + 0.786858 0.059541 + 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0.577097 -0.013374 + 0.593941 -0.012526 + 0.610767 -0.011702 + 0.627590 -0.010909 + 0.644419 -0.010150 + 0.661294 -0.009404 + 0.678160 -0.008664 + 0.694999 -0.007942 + 0.711803 -0.007256 + 0.728591 -0.006620 + 0.745420 -0.006024 + 0.762267 -0.005450 + 0.779086 -0.004900 + 0.795889 -0.004396 + 0.812688 -0.003931 + 0.829477 -0.003519 + 0.846265 -0.003150 + 0.863023 -0.002838 + 0.879771 -0.002589 + 0.896536 -0.002403 + 0.913325 -0.002267 + 0.930138 -0.002172 + 0.946916 -0.002104 + 0.963521 -0.002061 + 0.979297 -0.001995 + 0.993038 -0.001895 + 1.000000 -0.001846 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid322.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid322.dat new file mode 100644 index 00000000..c98ef0de --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid322.dat @@ -0,0 +1,141 @@ +MID 322 (c)Slobodan Midic for Re numbers from 80k up to 400k + 1.000000 0.000784 + 0.993487 0.001862 + 0.980401 0.003993 + 0.964770 0.006530 + 0.948280 0.009195 + 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b/aerosandbox/geometry/airfoil/airfoil_database/mid327-12.dat @@ -0,0 +1,203 @@ +MID 327 12% (c) Slobodan Midic + 1.000000 0.000659 + 0.996559 0.001200 + 0.989553 0.002319 + 0.980008 0.003898 + 0.968643 0.005793 + 0.956246 0.007879 + 0.943447 0.010058 + 0.930483 0.012282 + 0.917506 0.014519 + 0.904552 0.016773 + 0.891549 0.019041 + 0.878530 0.021314 + 0.865525 0.023588 + 0.852504 0.025858 + 0.839513 0.028121 + 0.826593 0.030356 + 0.813623 0.032579 + 0.800722 0.034778 + 0.787872 0.036932 + 0.774967 0.039069 + 0.762111 0.041171 + 0.749291 0.043232 + 0.736452 0.045258 + 0.723618 0.047249 + 0.710824 0.049195 + 0.698018 0.051099 + 0.685225 0.052962 + 0.672463 0.054773 + 0.659697 0.056536 + 0.646923 0.058253 + 0.634184 0.059916 + 0.621462 0.061522 + 0.608713 0.063075 + 0.595957 0.064578 + 0.583239 0.066023 + 0.570517 0.067408 + 0.557763 0.068741 + 0.545009 0.070021 + 0.532263 0.071243 + 0.519496 0.072412 + 0.506718 0.073529 + 0.493958 0.074592 + 0.481210 0.075596 + 0.468470 0.076542 + 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R/C Soaring models as for F3B/J or +similar. + +As the drag CD at lift of CL=0-1 is relative small it's good for +task A Duration, excelent for task B Distance and very good +for task C Speed in Multi Task Thermal Soaring Gliders F3B. +Caracteristics of model can be controled using flaps or +flaperons, but only with small deflections, because airfoil regard +good caracteristics without any controle of trailing edge. With +positive deflection of flaps more than +5 degre (down) max. +lift increase but drag increase very strong so as a good brake. + +Slobodan Midic +Novi Sad, Jan. 2010. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid32_F3J_F5J.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid32_F3J_F5J.dat new file mode 100644 index 00000000..6f85d58d --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid32_F3J_F5J.dat @@ -0,0 +1,161 @@ +MID-32 F3J F5J (C)Slobodan Midic + 1.000000 0.000306 + 0.994054 0.001052 + 0.982050 0.002647 + 0.968503 0.004480 + 0.954662 0.006369 + 0.940783 0.008258 + 0.926901 0.010132 + 0.913016 0.011983 + 0.899128 0.013810 + 0.885240 0.015613 + 0.871350 0.017394 + 0.857464 0.019150 + 0.843575 0.020885 + 0.829689 0.022597 + 0.815801 0.024284 + 0.801909 0.025946 + 0.788021 0.027582 + 0.774128 0.029190 + 0.760232 0.030770 + 0.746336 0.032321 + 0.732435 0.033838 + 0.718530 0.035327 + 0.704627 0.036783 + 0.690721 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b/aerosandbox/geometry/airfoil/airfoil_database/mid33_F3J_F5J.dat @@ -0,0 +1,141 @@ +MID-33 F3J F5J (C)Slobodan Midic + 1.000000 0.000677 + 0.993180 0.001463 + 0.978974 0.003175 + 0.963458 0.005071 + 0.947570 0.007019 + 0.931669 0.008948 + 0.915770 0.010856 + 0.899878 0.012727 + 0.883971 0.014571 + 0.868061 0.016385 + 0.852145 0.018173 + 0.836223 0.019933 + 0.820301 0.021668 + 0.804380 0.023374 + 0.788456 0.025051 + 0.772537 0.026695 + 0.756597 0.028313 + 0.740680 0.029901 + 0.724766 0.031446 + 0.708823 0.032964 + 0.692895 0.034449 + 0.676971 0.035895 + 0.661042 0.037304 + 0.645121 0.038672 + 0.629201 0.039995 + 0.613273 0.041275 + 0.597348 0.042511 + 0.581425 0.043699 + 0.565497 0.044841 + 0.549575 0.045933 + 0.533640 0.046975 + 0.517715 0.047969 + 0.501796 0.048906 + 0.485870 0.049788 + 0.469950 0.050613 + 0.454034 0.051379 + 0.438116 0.052081 + 0.422194 0.052723 + 0.406302 0.053297 + 0.390389 0.053797 + 0.374496 0.054230 + 0.358618 0.054578 + 0.342731 0.054848 + 0.326867 0.055032 + 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a/aerosandbox/geometry/airfoil/airfoil_database/mid343.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid343.dat new file mode 100644 index 00000000..433bc864 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid343.dat @@ -0,0 +1,141 @@ +MID 343 11% (c)Slobodan Midic - Allround R/C glider + 1.000000 0.001094 + 0.993528 0.002713 + 0.980906 0.005751 + 0.965842 0.009225 + 0.949690 0.012777 + 0.933172 0.016246 + 0.916503 0.019587 + 0.899754 0.022810 + 0.882932 0.025921 + 0.866053 0.028938 + 0.849115 0.031872 + 0.832128 0.034740 + 0.815097 0.037553 + 0.798086 0.040315 + 0.781132 0.042991 + 0.764179 0.045572 + 0.747174 0.048080 + 0.730135 0.050534 + 0.713101 0.052928 + 0.696067 0.055255 + 0.679036 0.057517 + 0.662008 0.059706 + 0.644980 0.061826 + 0.627963 0.063870 + 0.610946 0.065833 + 0.593932 0.067718 + 0.576930 0.069516 + 0.559924 0.071228 + 0.542924 0.072851 + 0.525934 0.074380 + 0.508945 0.075815 + 0.491977 0.077148 + 0.475019 0.078370 + 0.458064 0.079486 + 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0.449196 -0.025343 + 0.465816 -0.024841 + 0.482424 -0.024333 + 0.499020 -0.023793 + 0.515647 -0.023238 + 0.532257 -0.022680 + 0.548856 -0.022090 + 0.565484 -0.021487 + 0.582095 -0.020881 + 0.598698 -0.020244 + 0.615327 -0.019596 + 0.631936 -0.018944 + 0.648544 -0.018262 + 0.665172 -0.017572 + 0.681776 -0.016876 + 0.698392 -0.016151 + 0.715016 -0.015425 + 0.731616 -0.014686 + 0.748241 -0.013924 + 0.764856 -0.013164 + 0.781462 -0.012380 + 0.798081 -0.011592 + 0.814664 -0.010794 + 0.831262 -0.009964 + 0.847815 -0.009115 + 0.864341 -0.008214 + 0.880844 -0.007271 + 0.897364 -0.006259 + 0.913946 -0.005231 + 0.930513 -0.004201 + 0.947056 -0.003178 + 0.963492 -0.002169 + 0.979322 -0.001213 + 0.993023 -0.000352 + 1.000000 0.000109 + +Airfoils for Blended body configuration +Date: Fri Mar 30, 2007 6:04 am ((PDT)) +For your wished data is: +- total mass: m=13+5 kg=18 kg (W=18*9.81=176.6 N) +and at cruise velocity: v=25 m/s +and say cl=0.6, and AR=10, needed wing surface S is: +S=2*W/(cl*rho*v2)=2*176.6/(0.6*1.293*252)=0.728 m2 +Average wing cord c is: c=sqrt(S/AR)=sqrt(0.782/10)=0.28 m. +Wing span b is: b=S/c=0.728/0.28=2.6 m. For trapeze wing with the cord tip to root ratio of r=0.7 root cord is (c)root=2*c/(1+r)=2*0.28/(1+0.7)=0.33 m, tip cord is (c)tip=0.23 m. +Re numbers are: (Re)aw=69000*c*v=69000*0.28*25=483000=483k, +(Re)root=569k, (Re)tip=397k. Say wing fly at about Re=500k. +At the stalling needed lift is: cl=2*W/(S*rho*vs2)=2*176.6/(0.728*1.293*182)=1.16, and Re number is: (Re)aw=348k. +Now we have all significant data to make a airfoil choice. +For straight rectangular wing we need airfoil with cm=0. +For arrow rectangular wing tip part of wing need to have cm>0, +inner part can be with cm<0. That must be calculate separately. I prefer the second type. +Also it's important the thickness of airfoil. I think 15% is enough for root, 10% for tip. +If so, we need an airfoil with: (a) cl=0.6 at Re=500k, and (b) cl=1.2 at Re=350k. I suggest you to try with MID 371 AW at root, MID 371 at tip, and interpolates airfoils between. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid371aw.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid371aw.dat new file mode 100644 index 00000000..fb624889 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid371aw.dat @@ -0,0 +1,160 @@ +MID 371AW 15% at root (c)Slobodan Midic + 1.000000 0.000109 + 0.993027 0.000386 + 0.979474 0.001001 + 0.964100 0.001906 + 0.948307 0.003153 + 0.932416 0.004724 + 0.916438 0.006601 + 0.900396 0.008751 + 0.884239 0.011127 + 0.868002 0.013672 + 0.851645 0.016340 + 0.835242 0.019082 + 0.818762 0.021884 + 0.802268 0.024708 + 0.785754 0.027558 + 0.769225 0.030407 + 0.752698 0.033258 + 0.736180 0.036099 + 0.719645 0.038924 + 0.703113 0.041740 + 0.686597 0.044531 + 0.670054 0.047304 + 0.653533 0.050062 + 0.637017 0.052785 + 0.620477 0.055492 + 0.603972 0.058167 + 0.587467 0.060804 + 0.570950 0.063411 + 0.554474 0.065970 + 0.537992 0.068476 + 0.521509 0.070934 + 0.505067 0.073324 + 0.488615 0.075642 + 0.472169 0.077891 + 0.455765 0.080047 + 0.439347 0.082109 + 0.422948 0.084075 + 0.406589 0.085914 + 0.390215 0.087633 + 0.373882 0.089215 + 0.357583 0.090635 + 0.341281 0.091897 + 0.325046 0.092972 + 0.308836 0.093835 + 0.292664 0.094488 + 0.276568 0.094879 + 0.260490 0.095008 + 0.244498 0.094851 + 0.228550 0.094360 + 0.212664 0.093548 + 0.196863 0.092356 + 0.181111 0.090785 + 0.165474 0.088805 + 0.149917 0.086391 + 0.134560 0.083535 + 0.119437 0.080210 + 0.104665 0.076371 + 0.090128 0.071890 + 0.075786 0.066716 + 0.061912 0.060974 + 0.049078 0.054734 + 0.037491 0.047773 + 0.027113 0.040092 + 0.018586 0.032613 + 0.012391 0.025990 + 0.008068 0.020367 + 0.005087 0.015627 + 0.002964 0.011659 + 0.001507 0.008230 + 0.000596 0.005151 + 0.000085 0.002319 + 0.000001 -0.000400 + 0.000585 -0.003338 + 0.001936 -0.006203 + 0.003884 -0.008948 + 0.006478 -0.011808 + 0.009973 -0.014909 + 0.014770 -0.018464 + 0.021507 -0.022485 + 0.030860 -0.026898 + 0.042956 -0.031213 + 0.057113 -0.035136 + 0.072276 -0.038498 + 0.087897 -0.041273 + 0.104047 -0.043694 + 0.120399 -0.045855 + 0.136736 -0.047919 + 0.153001 -0.049712 + 0.169215 -0.051231 + 0.185430 -0.052429 + 0.201751 -0.053396 + 0.218027 -0.054108 + 0.234427 -0.054593 + 0.250814 -0.054905 + 0.267238 -0.055005 + 0.283750 -0.054972 + 0.300199 -0.054794 + 0.316720 -0.054465 + 0.333259 -0.054044 + 0.349749 -0.053496 + 0.366323 -0.052838 + 0.382883 -0.052114 + 0.399416 -0.051285 + 0.416027 -0.050381 + 0.432615 -0.049431 + 0.449187 -0.048403 + 0.465808 -0.047326 + 0.482416 -0.046221 + 0.499012 -0.045062 + 0.515639 -0.043868 + 0.532250 -0.042655 + 0.548849 -0.041393 + 0.565477 -0.040102 + 0.582088 -0.038798 + 0.598692 -0.037449 + 0.615321 -0.036078 + 0.631930 -0.034696 + 0.648538 -0.033273 + 0.665167 -0.031833 + 0.681771 -0.030382 + 0.698387 -0.028892 + 0.715012 -0.027394 + 0.731612 -0.025880 + 0.748237 -0.024333 + 0.764852 -0.022786 + 0.781459 -0.021210 + 0.798078 -0.019629 + 0.814661 -0.018040 + 0.831260 -0.016415 + 0.847813 -0.014779 + 0.864339 -0.013093 + 0.880842 -0.011378 + 0.897363 -0.009611 + 0.913945 -0.007869 + 0.930512 -0.006184 + 0.947055 -0.004577 + 0.963492 -0.003063 + 0.979322 -0.001695 + 0.993023 -0.000512 + 1.000000 0.000109 + +Airfoils for Blended body configuration +Date: Fri Mar 30, 2007 6:04 am ((PDT)) +For your wished data is: +- total mass: m=13+5 kg=18 kg (W=18*9.81=176.6 N) +and at cruise velocity: v=25 m/s +and say cl=0.6, and AR=10, needed wing surface S is: +S=2*W/(cl*rho*v2)=2*176.6/(0.6*1.293*252)=0.728 m2 +Average wing cord c is: c=sqrt(S/AR)=sqrt(0.782/10)=0.28 m. +Wing span b is: b=S/c=0.728/0.28=2.6 m. For trapeze wing with the cord tip to root ratio of r=0.7 root cord is (c)root=2*c/(1+r)=2*0.28/(1+0.7)=0.33 m, tip cord is (c)tip=0.23 m. +Re numbers are: (Re)aw=69000*c*v=69000*0.28*25=483000=483k, +(Re)root=569k, (Re)tip=397k. Say wing fly at about Re=500k. +At the stalling needed lift is: cl=2*W/(S*rho*vs2)=2*176.6/(0.728*1.293*182)=1.16, and Re number is: (Re)aw=348k. +Now we have all significant data to make a airfoil choice. +For straight rectangular wing we need airfoil with cm=0. +For arrow rectangular wing tip part of wing need to have cm>0, +inner part can be with cm<0. That must be calculate separately. I prefer the second type. +Also it's important the thickness of airfoil. I think 15% is enough for root, 10% for tip. +If so, we need an airfoil with: (a) cl=0.6 at Re=500k, and (b) cl=1.2 at Re=350k. I suggest you to try with MID 371 AW at root, MID 371 at tip, and interpolates airfoils between. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid37_F5Js.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid37_F5Js.dat new file mode 100644 index 00000000..cf04e915 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid37_F5Js.dat @@ -0,0 +1,142 @@ +MID-37 F5Js (C)Slobodan_Midic + 1.000000 0.000500 + 0.993189 0.001207 + 0.979754 0.002717 + 0.964178 0.004407 + 0.948018 0.006155 + 0.931780 0.007882 + 0.915534 0.009624 + 0.899270 0.011414 + 0.883008 0.013213 + 0.866724 0.014977 + 0.850433 0.016725 + 0.834131 0.018441 + 0.817803 0.020147 + 0.801496 0.021830 + 0.785167 0.023492 + 0.768850 0.025137 + 0.752527 0.026757 + 0.736207 0.028357 + 0.719899 0.029928 + 0.703583 0.031472 + 0.687277 0.032986 + 0.670969 0.034467 + 0.654653 0.035920 + 0.638347 0.037338 + 0.622030 0.038722 + 0.605713 0.040077 + 0.589403 0.041394 + 0.573083 0.042677 + 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0.004473 + 0.788361 0.004561 + 0.804324 0.004605 + 0.820287 0.004595 + 0.836238 0.004535 + 0.852167 0.004410 + 0.868106 0.004225 + 0.884014 0.003971 + 0.899897 0.003637 + 0.915784 0.003218 + 0.931655 0.002714 + 0.947494 0.002117 + 0.963353 0.001424 + 0.978797 0.000664 + 0.993117 -0.000116 + 1.000000 -0.000500 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid38_F5Js.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid38_F5Js.dat new file mode 100644 index 00000000..1a2687ec --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid38_F5Js.dat @@ -0,0 +1,141 @@ +MID-38 F5Js (C)Slobodan_Midic + 1.000000 0.000499 + 0.993202 0.001140 + 0.978910 0.002600 + 0.963699 0.004099 + 0.948061 0.005640 + 0.932427 0.007155 + 0.916757 0.008688 + 0.901092 0.010260 + 0.885427 0.011848 + 0.869768 0.013406 + 0.854073 0.014951 + 0.838399 0.016470 + 0.822683 0.017978 + 0.806991 0.019472 + 0.791293 0.020946 + 0.775581 0.022407 + 0.759887 0.023848 + 0.744177 0.025272 + 0.728483 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b/aerosandbox/geometry/airfoil/airfoil_database/mid393ul25.dat @@ -0,0 +1,141 @@ +MID 393 UL 2.5x15 camber 2.5% (c)Slobodan Midic + 1.000000 0.001386 + 0.992609 0.002905 + 0.979701 0.005493 + 0.964776 0.008451 + 0.948025 0.011738 + 0.929835 0.015264 + 0.910626 0.018957 + 0.890757 0.022743 + 0.870466 0.026571 + 0.849915 0.030413 + 0.829178 0.034249 + 0.808307 0.038078 + 0.787353 0.041890 + 0.766352 0.045672 + 0.745330 0.049422 + 0.724324 0.053119 + 0.703347 0.056760 + 0.682424 0.060316 + 0.661490 0.063790 + 0.640566 0.067188 + 0.619689 0.070497 + 0.598898 0.073698 + 0.578209 0.076774 + 0.557630 0.079712 + 0.537165 0.082493 + 0.516816 0.085109 + 0.496587 0.087549 + 0.476482 0.089807 + 0.456513 0.091875 + 0.436686 0.093742 + 0.417012 0.095399 + 0.397500 0.096838 + 0.378167 0.098048 + 0.359028 0.099020 + 0.340113 0.099743 + 0.321451 0.100205 + 0.303070 0.100389 + 0.284968 0.100280 + 0.267181 0.099880 + 0.249747 0.099170 + 0.232672 0.098138 + 0.215963 0.096772 + 0.199617 0.095072 + 0.183667 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diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid39_F5Js.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid39_F5Js.dat new file mode 100644 index 00000000..c3159828 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid39_F5Js.dat @@ -0,0 +1,142 @@ +MID_39 F5Js (C)Slobodan Midic + 1.000000 0.000499 + 0.993189 0.001075 + 0.979754 0.002311 + 0.964178 0.003696 + 0.948018 0.005132 + 0.931780 0.006554 + 0.915534 0.007993 + 0.899270 0.009473 + 0.883008 0.010967 + 0.866724 0.012433 + 0.850433 0.013887 + 0.834131 0.015316 + 0.817803 0.016740 + 0.801496 0.018147 + 0.785167 0.019537 + 0.768850 0.020915 + 0.752527 0.022274 + 0.736207 0.023616 + 0.719899 0.024935 + 0.703583 0.026233 + 0.687277 0.027508 + 0.670969 0.028755 + 0.654653 0.029980 + 0.638347 0.031176 + 0.622030 0.032345 + 0.605713 0.033491 + 0.589403 0.034607 + 0.573083 0.035694 + 0.556772 0.036754 + 0.540469 0.037777 + 0.524158 0.038769 + 0.507862 0.039726 + 0.491572 0.040641 + 0.475278 0.041517 + 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0.640367 -0.006984 + 0.660953 -0.005607 + 0.681476 -0.004348 + 0.701947 -0.003213 + 0.722373 -0.002206 + 0.742761 -0.001333 + 0.763126 -0.000597 + 0.783484 -0.000001 + 0.803850 0.000457 + 0.824234 0.000779 + 0.844643 0.000967 + 0.865070 0.001028 + 0.885513 0.000960 + 0.905935 0.000788 + 0.926088 0.000572 + 0.945409 0.000351 + 0.963230 0.000119 + 0.978973 -0.000107 + 0.992341 -0.000323 + 1.000000 -0.000494 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid405e.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid405e.dat new file mode 100644 index 00000000..092778d7 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid405e.dat @@ -0,0 +1,141 @@ +MID 405e (c)Slobodan Midic for very slow flying devices (modifications of the airfoil DAE11) + 1.000000 0.001373 + 0.992367 0.002782 + 0.977823 0.005435 + 0.961979 0.008408 + 0.945883 0.011578 + 0.929812 0.014941 + 0.913740 0.018499 + 0.897669 0.022233 + 0.881602 0.026129 + 0.865545 0.030172 + 0.849492 0.034354 + 0.833434 0.038660 + 0.817376 0.043073 + 0.801325 0.047583 + 0.785277 0.052183 + 0.769235 0.056863 + 0.753184 0.061618 + 0.737110 0.066437 + 0.721006 0.071298 + 0.704883 0.076178 + 0.688801 0.081025 + 0.672777 0.085803 + 0.656816 0.090471 + 0.640917 0.094986 + 0.625067 0.099305 + 0.609251 0.103392 + 0.593452 0.107216 + 0.577654 0.110749 + 0.561838 0.113971 + 0.545975 0.116875 + 0.530049 0.119464 + 0.514061 0.121745 + 0.498010 0.123726 + 0.481906 0.125413 + 0.465764 0.126812 + 0.449584 0.127926 + 0.433377 0.128761 + 0.417150 0.129318 + 0.400908 0.129601 + 0.384660 0.129613 + 0.368414 0.129353 + 0.352175 0.128822 + 0.335952 0.128017 + 0.319750 0.126940 + 0.303580 0.125586 + 0.287446 0.123950 + 0.271356 0.122032 + 0.255324 0.119823 + 0.239353 0.117319 + 0.223463 0.114511 + 0.207661 0.111392 + 0.191962 0.107952 + 0.176385 0.104179 + 0.160949 0.100059 + 0.145678 0.095580 + 0.130603 0.090728 + 0.115758 0.085486 + 0.101186 0.079842 + 0.086946 0.073786 + 0.073110 0.067316 + 0.059782 0.060444 + 0.047110 0.053192 + 0.035323 0.045618 + 0.024819 0.037858 + 0.016221 0.030266 + 0.009993 0.023396 + 0.005924 0.017634 + 0.003378 0.012947 + 0.001810 0.009101 + 0.000854 0.005890 + 0.000377 0.003167 + 0.000092 0.000802 + 0.000125 -0.001424 + 0.000857 -0.003870 + 0.002334 -0.006107 + 0.004538 -0.008136 + 0.007546 -0.010080 + 0.011676 -0.012008 + 0.017511 -0.013779 + 0.025860 -0.015212 + 0.037196 -0.016174 + 0.050973 -0.016628 + 0.066137 -0.016641 + 0.082055 -0.016345 + 0.098339 -0.015850 + 0.114714 -0.015191 + 0.131119 -0.014342 + 0.147616 -0.013318 + 0.164194 -0.012161 + 0.180820 -0.010905 + 0.197478 -0.009563 + 0.214171 -0.008152 + 0.230881 -0.006690 + 0.247602 -0.005180 + 0.264335 -0.003631 + 0.281087 -0.002051 + 0.297852 -0.000445 + 0.314634 0.001174 + 0.331424 0.002803 + 0.348214 0.004431 + 0.364989 0.006048 + 0.381753 0.007648 + 0.398500 0.009222 + 0.415235 0.010763 + 0.431951 0.012263 + 0.448658 0.013714 + 0.465352 0.015109 + 0.482031 0.016439 + 0.498700 0.017699 + 0.515357 0.018880 + 0.532001 0.019974 + 0.548635 0.020974 + 0.565258 0.021874 + 0.581872 0.022665 + 0.598468 0.023341 + 0.615057 0.023894 + 0.631628 0.024315 + 0.648189 0.024600 + 0.664738 0.024740 + 0.681276 0.024732 + 0.697816 0.024571 + 0.714352 0.024260 + 0.730888 0.023798 + 0.747423 0.023189 + 0.763951 0.022432 + 0.780472 0.021524 + 0.796993 0.020473 + 0.813504 0.019275 + 0.830009 0.017935 + 0.846509 0.016453 + 0.862999 0.014833 + 0.879481 0.013074 + 0.895959 0.011181 + 0.912428 0.009160 + 0.928889 0.007011 + 0.945332 0.004739 + 0.961714 0.002360 + 0.977754 -0.000077 + 0.992294 -0.002374 + 1.000000 -0.003626 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid405w2.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid405w2.dat new file mode 100644 index 00000000..276ca30a --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid405w2.dat @@ -0,0 +1,145 @@ +MID 405w2 (c)Slobodan Midic for very slow flying devices (modifications of the airfoil DAE11) + 1.000000 0.008874 + 0.992388 0.010201 + 0.977844 0.012700 + 0.961999 0.015506 + 0.945902 0.018510 + 0.929831 0.021708 + 0.913758 0.025104 + 0.897687 0.028677 + 0.881620 0.032414 + 0.865562 0.036300 + 0.849509 0.040327 + 0.833450 0.044480 + 0.817392 0.048742 + 0.801340 0.053102 + 0.785292 0.057555 + 0.769250 0.062089 + 0.753199 0.066700 + 0.737124 0.071376 + 0.721019 0.076095 + 0.704896 0.080836 + 0.688813 0.085546 + 0.672789 0.090188 + 0.656828 0.094723 + 0.640929 0.099107 + 0.625078 0.103297 + 0.609262 0.107256 + 0.593462 0.110954 + 0.577664 0.114364 + 0.561848 0.117463 + 0.545984 0.120245 + 0.530058 0.122713 + 0.514070 0.124875 + 0.498019 0.126737 + 0.481914 0.128307 + 0.465772 0.129590 + 0.449591 0.130589 + 0.433384 0.131310 + 0.417157 0.131754 + 0.400914 0.131926 + 0.384666 0.131829 + 0.368420 0.131460 + 0.352181 0.130822 + 0.335958 0.129912 + 0.319755 0.128731 + 0.303585 0.127275 + 0.287450 0.125537 + 0.271360 0.123520 + 0.255328 0.121214 + 0.239356 0.118614 + 0.223466 0.115712 + 0.207664 0.112500 + 0.191965 0.108969 + 0.176388 0.105108 + 0.160952 0.100901 + 0.145680 0.096337 + 0.130605 0.091402 + 0.115760 0.086080 + 0.101187 0.080358 + 0.086947 0.074227 + 0.073111 0.067684 + 0.059783 0.060743 + 0.047110 0.053426 + 0.035323 0.045793 + 0.024819 0.037980 + 0.016221 0.030345 + 0.009993 0.023444 + 0.005924 0.017663 + 0.003378 0.012963 + 0.001810 0.009110 + 0.000854 0.005894 + 0.000377 0.003169 + 0.000092 0.000802 + 0.000125 -0.001424 + 0.000857 -0.003874 + 0.002334 -0.006118 + 0.004538 -0.008158 + 0.007546 -0.010117 + 0.011676 -0.012065 + 0.017511 -0.013865 + 0.025860 -0.015340 + 0.037196 -0.016359 + 0.050973 -0.016883 + 0.066136 -0.016974 + 0.082054 -0.016760 + 0.098338 -0.016351 + 0.114712 -0.015779 + 0.131117 -0.015020 + 0.147614 -0.014086 + 0.164191 -0.013022 + 0.180817 -0.011859 + 0.197475 -0.010613 + 0.214168 -0.009299 + 0.230878 -0.007935 + 0.247598 -0.006525 + 0.264331 -0.005077 + 0.281083 -0.003600 + 0.297847 -0.002098 + 0.314629 -0.000585 + 0.331419 0.000937 + 0.348208 0.002456 + 0.364983 0.003963 + 0.381747 0.005452 + 0.398494 0.006912 + 0.415228 0.008339 + 0.431944 0.009723 + 0.448651 0.011057 + 0.465344 0.012334 + 0.482023 0.013544 + 0.498691 0.014682 + 0.515348 0.015740 + 0.531992 0.016710 + 0.548626 0.017583 + 0.565248 0.018355 + 0.581862 0.019017 + 0.598457 0.019562 + 0.615046 0.019983 + 0.631616 0.020269 + 0.648177 0.020419 + 0.664726 0.020421 + 0.681264 0.020275 + 0.697803 0.019973 + 0.714339 0.019520 + 0.730874 0.018914 + 0.747409 0.018158 + 0.763936 0.017254 + 0.780457 0.016196 + 0.796978 0.014993 + 0.813488 0.013642 + 0.829993 0.012148 + 0.846492 0.010508 + 0.862982 0.008729 + 0.879463 0.006810 + 0.895941 0.004754 + 0.912410 0.002569 + 0.928870 0.000253 + 0.945313 -0.002187 + 0.961694 -0.004735 + 0.977733 -0.007342 + 0.992273 -0.009792 + 1.000000 -0.011126 + +Airfoils are developed for Raynolds numbers from Re=300k up to Re=1M. In that range +lift is very high (CL up to 1.8), and drag is low. At Mid 405e, and at Re=500k power +factor is CL^1.5/CD=180, and CL/CD=142, both at about A0A=7 deg. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid406w2.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid406w2.dat new file mode 100644 index 00000000..cb262354 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid406w2.dat @@ -0,0 +1,145 @@ +MID 406w2 (c)Slobodan Midic for very slow flying devices (modifications of the airfoil DAE11) + 1.000000 0.008893 + 0.992384 0.010129 + 0.977840 0.012464 + 0.961994 0.015109 + 0.945898 0.017970 + 0.929827 0.021053 + 0.913755 0.024360 + 0.897683 0.027871 + 0.881616 0.031571 + 0.865558 0.035446 + 0.849506 0.039489 + 0.833447 0.043682 + 0.817389 0.048008 + 0.801338 0.052457 + 0.785290 0.057023 + 0.769246 0.061693 + 0.753195 0.066463 + 0.737121 0.071322 + 0.721017 0.076245 + 0.704894 0.081210 + 0.688812 0.086163 + 0.672788 0.091063 + 0.656827 0.095871 + 0.640928 0.100539 + 0.625078 0.105019 + 0.609262 0.109274 + 0.593463 0.113269 + 0.577665 0.116974 + 0.561849 0.120366 + 0.545985 0.123440 + 0.530059 0.126193 + 0.514071 0.128636 + 0.498021 0.130776 + 0.481917 0.132618 + 0.465774 0.134166 + 0.449595 0.135423 + 0.433388 0.136396 + 0.417161 0.137083 + 0.400919 0.137488 + 0.384671 0.137613 + 0.368424 0.137456 + 0.352185 0.137016 + 0.335962 0.136290 + 0.319760 0.135280 + 0.303590 0.133977 + 0.287456 0.132376 + 0.271365 0.130476 + 0.255333 0.128266 + 0.239363 0.125742 + 0.223473 0.122893 + 0.207671 0.119711 + 0.191972 0.116181 + 0.176394 0.112295 + 0.160958 0.108030 + 0.145686 0.103377 + 0.130610 0.098313 + 0.115765 0.092820 + 0.101193 0.086880 + 0.086953 0.080491 + 0.073116 0.073647 + 0.059787 0.066356 + 0.047115 0.058632 + 0.035327 0.050521 + 0.024823 0.042151 + 0.016224 0.033878 + 0.009996 0.026302 + 0.005926 0.019899 + 0.003380 0.014673 + 0.001811 0.010370 + 0.000855 0.006757 + 0.000377 0.003705 + 0.000092 0.001013 + 0.000125 -0.001649 + 0.000856 -0.004925 + 0.002332 -0.007943 + 0.004536 -0.010760 + 0.007543 -0.013511 + 0.011672 -0.016311 + 0.017506 -0.019066 + 0.025854 -0.021630 + 0.037189 -0.023859 + 0.050965 -0.025622 + 0.066127 -0.026887 + 0.082044 -0.027753 + 0.098327 -0.028320 + 0.114701 -0.028618 + 0.131106 -0.028630 + 0.147601 -0.028384 + 0.164178 -0.027931 + 0.180803 -0.027310 + 0.197460 -0.026542 + 0.214153 -0.025646 + 0.230863 -0.024644 + 0.247583 -0.023544 + 0.264316 -0.022355 + 0.281068 -0.021090 + 0.297832 -0.019753 + 0.314614 -0.018361 + 0.331404 -0.016917 + 0.348194 -0.015434 + 0.364969 -0.013922 + 0.381731 -0.012387 + 0.398478 -0.010842 + 0.415213 -0.009290 + 0.431929 -0.007742 + 0.448636 -0.006207 + 0.465330 -0.004688 + 0.482009 -0.003196 + 0.498678 -0.001735 + 0.515335 -0.000315 + 0.531980 0.001061 + 0.548614 0.002384 + 0.565236 0.003651 + 0.581851 0.004852 + 0.598446 0.005980 + 0.615036 0.007019 + 0.631608 0.007954 + 0.648168 0.008777 + 0.664718 0.009470 + 0.681256 0.010023 + 0.697797 0.010422 + 0.714333 0.010668 + 0.730869 0.010753 + 0.747405 0.010676 + 0.763934 0.010436 + 0.780454 0.010024 + 0.796975 0.009449 + 0.813486 0.008703 + 0.829992 0.007791 + 0.846492 0.006712 + 0.862982 0.005468 + 0.879464 0.004055 + 0.895943 0.002476 + 0.912411 0.000739 + 0.928872 -0.001162 + 0.945316 -0.003224 + 0.961698 -0.005431 + 0.977736 -0.007728 + 0.992276 -0.009914 + 1.000000 -0.011107 + +Airfoils are developed for Raynolds numbers from Re=300k up to Re=1M. In that range +lift is very high (CL up to 1.8), and drag is low. At Mid 405e, and at Re=500k power +factor is CL^1.5/CD=180, and CL/CD=142, both at about A0A=7 deg. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid415.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid415.dat new file mode 100644 index 00000000..99a1a152 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid415.dat @@ -0,0 +1,151 @@ +MID 415 mid393 modified 0.038 camber instead of 0.05 (c)Slobodan Midic + 1.000000 0.001905 + 0.992609 0.003799 + 0.979702 0.007010 + 0.964778 0.010653 + 0.948027 0.014669 + 0.929837 0.018938 + 0.910628 0.023360 + 0.890760 0.027848 + 0.870470 0.032344 + 0.849919 0.036819 + 0.829182 0.041252 + 0.808312 0.045643 + 0.787358 0.049983 + 0.766357 0.054262 + 0.745336 0.058480 + 0.724330 0.062617 + 0.703353 0.066670 + 0.682430 0.070614 + 0.661497 0.074451 + 0.640573 0.078192 + 0.619696 0.081823 + 0.598905 0.085327 + 0.578216 0.088686 + 0.557638 0.091886 + 0.537173 0.094912 + 0.516824 0.097753 + 0.496595 0.100398 + 0.476490 0.102837 + 0.456521 0.105060 + 0.436694 0.107054 + 0.417020 0.108809 + 0.397508 0.110315 + 0.378175 0.111558 + 0.359036 0.112529 + 0.340121 0.113217 + 0.321459 0.113606 + 0.303078 0.113680 + 0.284976 0.113423 + 0.267190 0.112838 + 0.249755 0.111902 + 0.232680 0.110605 + 0.215971 0.108932 + 0.199624 0.106884 + 0.183674 0.104465 + 0.168162 0.101686 + 0.153148 0.098558 + 0.138684 0.095097 + 0.124844 0.091330 + 0.111690 0.087286 + 0.099293 0.083010 + 0.087717 0.078559 + 0.077024 0.074007 + 0.067252 0.069426 + 0.058418 0.064906 + 0.050521 0.060493 + 0.043512 0.056210 + 0.037318 0.052072 + 0.031857 0.048094 + 0.027040 0.044293 + 0.022796 0.040667 + 0.019065 0.037203 + 0.015789 0.033886 + 0.012925 0.030691 + 0.010448 0.027589 + 0.008325 0.024564 + 0.006512 0.021616 + 0.004959 0.018751 + 0.003633 0.015967 + 0.002519 0.013256 + 0.001615 0.010609 + 0.000919 0.008022 + 0.000436 0.005500 + 0.000174 0.003047 + 0.000142 0.000659 + 0.000348 -0.001741 + 0.000798 -0.004164 + 0.001508 -0.006627 + 0.002526 -0.009070 + 0.003918 -0.011445 + 0.005714 -0.013693 + 0.007897 -0.015755 + 0.010438 -0.017588 + 0.013317 -0.019191 + 0.016520 -0.020606 + 0.020051 -0.021903 + 0.023946 -0.023134 + 0.028257 -0.024331 + 0.033061 -0.025514 + 0.038449 -0.026698 + 0.044548 -0.027880 + 0.051516 -0.029060 + 0.059553 -0.030245 + 0.068890 -0.031432 + 0.079792 -0.032606 + 0.092476 -0.033765 + 0.107043 -0.034839 + 0.123484 -0.035781 + 0.141540 -0.036562 + 0.160854 -0.037158 + 0.180986 -0.037554 + 0.201638 -0.037748 + 0.222580 -0.037729 + 0.243750 -0.037507 + 0.265088 -0.037094 + 0.286607 -0.036510 + 0.308266 -0.035779 + 0.330081 -0.034913 + 0.352002 -0.033938 + 0.374025 -0.032861 + 0.396100 -0.031707 + 0.418208 -0.030468 + 0.440327 -0.029164 + 0.462425 -0.027787 + 0.484515 -0.026345 + 0.506559 -0.024835 + 0.528595 -0.023251 + 0.550633 -0.021595 + 0.572742 -0.019856 + 0.594949 -0.018069 + 0.617160 -0.016256 + 0.639302 -0.014442 + 0.661346 -0.012650 + 0.683246 -0.010894 + 0.704998 -0.009191 + 0.726577 -0.007552 + 0.747975 -0.006006 + 0.769190 -0.004563 + 0.790210 -0.003244 + 0.811045 -0.002060 + 0.831666 -0.001027 + 0.852065 -0.000155 + 0.872186 0.000543 + 0.891952 0.001059 + 0.911207 0.001379 + 0.929790 0.001484 + 0.947489 0.001376 + 0.963985 0.001100 + 0.978932 0.000701 + 0.992101 0.000234 + 1.000000 -0.000091 + + + +Following is mid 393 modified : +0.038 camber instead of 0.05 +Cd min 0.0064 at Cl 0.55 +reduced pitch moment + + Posted by: "plxdesi" plxdesi AT yahoo.com plxdesi + Date: Mon Mar 26, 2007 2:53 pm ((PDT)) \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid44a.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid44a.dat new file mode 100644 index 00000000..344ccad2 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid44a.dat @@ -0,0 +1,142 @@ +MID 44a #Slobodan Midic, F5K-GPS Triangle (min. Cd at Cl=0.2 at Re=200k) wing root + 1.000000 0.000532 + 0.993189 0.001139 + 0.979754 0.002453 + 0.964178 0.003930 + 0.948018 0.005475 + 0.931780 0.007016 + 0.915534 0.008592 + 0.899270 0.010229 + 0.883008 0.011894 + 0.866724 0.013539 + 0.850433 0.015182 + 0.834131 0.016807 + 0.817803 0.018434 + 0.801496 0.020050 + 0.785167 0.021656 + 0.768850 0.023254 + 0.752527 0.024835 + 0.736207 0.026405 + 0.719899 0.027954 + 0.703583 0.029484 + 0.687277 0.030993 + 0.670969 0.032476 + 0.654653 0.033939 + 0.638347 0.035373 + 0.622030 0.036782 + 0.605713 0.038172 + 0.589403 0.039529 + 0.573083 0.040859 + 0.556772 0.042163 + 0.540469 0.043430 + 0.524158 0.044664 + 0.507862 0.045862 + 0.491572 0.047017 + 0.475278 0.048128 + 0.459003 0.049193 + 0.442732 0.050203 + 0.426465 0.051159 + 0.410222 0.052054 + 0.393982 0.052879 + 0.377762 0.053633 + 0.361566 0.054300 + 0.345335 0.054886 + 0.329151 0.055398 + 0.313026 0.055796 + 0.296882 0.056084 + 0.280810 0.056261 + 0.264765 0.056286 + 0.248711 0.056180 + 0.232762 0.055919 + 0.216823 0.055476 + 0.200954 0.054859 + 0.185166 0.054024 + 0.169423 0.052972 + 0.153794 0.051676 + 0.138267 0.050119 + 0.122908 0.048266 + 0.107736 0.046090 + 0.092805 0.043538 + 0.078222 0.040594 + 0.064074 0.037177 + 0.050629 0.033283 + 0.038131 0.028900 + 0.027190 0.024201 + 0.018489 0.019594 + 0.012188 0.015491 + 0.007838 0.012003 + 0.004935 0.009027 + 0.002834 0.006400 + 0.001201 0.003997 + 0.000244 0.001749 + -0.000000 -0.000023 + 0.000010 -0.000343 + 0.000321 -0.002021 + 0.001362 -0.004074 + 0.003267 -0.006052 + 0.006091 -0.008115 + 0.010289 -0.010302 + 0.016997 -0.012787 + 0.027326 -0.015593 + 0.040505 -0.018164 + 0.055163 -0.020256 + 0.070298 -0.021865 + 0.085678 -0.023062 + 0.101243 -0.023938 + 0.116916 -0.024556 + 0.132659 -0.024955 + 0.148446 -0.025167 + 0.164281 -0.025220 + 0.180150 -0.025133 + 0.196045 -0.024924 + 0.211966 -0.024605 + 0.227900 -0.024194 + 0.243871 -0.023698 + 0.259859 -0.023137 + 0.275854 -0.022517 + 0.291889 -0.021847 + 0.307910 -0.021142 + 0.323935 -0.020397 + 0.339984 -0.019621 + 0.356023 -0.018832 + 0.372064 -0.018022 + 0.388109 -0.017196 + 0.404158 -0.016365 + 0.420205 -0.015521 + 0.436240 -0.014679 + 0.452264 -0.013839 + 0.468293 -0.013004 + 0.484313 -0.012176 + 0.500332 -0.011359 + 0.516354 -0.010550 + 0.532358 -0.009757 + 0.548376 -0.008982 + 0.564385 -0.008220 + 0.580386 -0.007480 + 0.596393 -0.006760 + 0.612403 -0.006061 + 0.628398 -0.005382 + 0.644388 -0.004735 + 0.660401 -0.004111 + 0.676396 -0.003509 + 0.692392 -0.002937 + 0.708405 -0.002385 + 0.724397 -0.001862 + 0.740393 -0.001372 + 0.756392 -0.000905 + 0.772375 -0.000475 + 0.788361 -0.000078 + 0.804324 0.000279 + 0.820287 0.000587 + 0.836238 0.000853 + 0.852167 0.001058 + 0.868106 0.001210 + 0.884014 0.001301 + 0.899897 0.001322 + 0.915784 0.001257 + 0.931655 0.001105 + 0.947494 0.000860 + 0.963353 0.000529 + 0.978797 0.000126 + 0.993117 -0.000305 + 1.000000 -0.000534 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid44b.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid44b.dat new file mode 100644 index 00000000..a8dd1529 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid44b.dat @@ -0,0 +1,161 @@ +MID 44b #Slobodan Midic, F5K-GPS Triangle (end of first panel) + 1.000000 0.000518 + 0.994102 0.001021 + 0.982178 0.002135 + 0.968934 0.003351 + 0.955182 0.004602 + 0.941316 0.005865 + 0.927432 0.007124 + 0.913560 0.008412 + 0.899680 0.009738 + 0.885790 0.011084 + 0.871891 0.012413 + 0.857965 0.013737 + 0.844052 0.015050 + 0.830114 0.016353 + 0.816167 0.017656 + 0.802229 0.018949 + 0.788279 0.020233 + 0.774327 0.021511 + 0.760390 0.022776 + 0.746442 0.024032 + 0.732503 0.025276 + 0.718569 0.026504 + 0.704629 0.027718 + 0.690696 0.028917 + 0.676766 0.030096 + 0.662824 0.031261 + 0.648895 0.032407 + 0.634965 0.033532 + 0.621018 0.034640 + 0.607079 0.035734 + 0.593153 0.036805 + 0.579214 0.037854 + 0.565271 0.038886 + 0.551347 0.039895 + 0.537417 0.040878 + 0.523482 0.041838 + 0.509557 0.042773 + 0.495639 0.043677 + 0.481717 0.044550 + 0.467795 0.045394 + 0.453892 0.046201 + 0.439982 0.046970 + 0.426073 0.047703 + 0.412183 0.048392 + 0.398295 0.049033 + 0.384409 0.049627 + 0.370548 0.050165 + 0.356682 0.050643 + 0.342785 0.051069 + 0.328937 0.051442 + 0.315127 0.051736 + 0.301289 0.051954 + 0.287476 0.052101 + 0.273726 0.052150 + 0.259938 0.052101 + 0.246174 0.051963 + 0.232478 0.051714 + 0.218774 0.051339 + 0.205105 0.050847 + 0.191503 0.050212 + 0.177903 0.049427 + 0.164370 0.048486 + 0.150881 0.047372 + 0.137477 0.046074 + 0.124151 0.044566 + 0.110948 0.042835 + 0.097883 0.040843 + 0.084971 0.038572 + 0.072337 0.035989 + 0.060002 0.033038 + 0.048104 0.029691 + 0.036856 0.025925 + 0.026605 0.021783 + 0.017992 0.017518 + 0.011528 0.013572 + 0.007203 0.010261 + 0.004368 0.007471 + 0.002408 0.005186 + 0.001064 0.003299 + 0.000262 0.001583 + 0.000000 0.000057 + 0.000229 -0.001483 + 0.001003 -0.003071 + 0.002405 -0.004610 + 0.004520 -0.006135 + 0.007499 -0.007770 + 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-0.002540 + 0.662112 -0.002091 + 0.676078 -0.001660 + 0.690047 -0.001253 + 0.704030 -0.000861 + 0.717995 -0.000488 + 0.731955 -0.000140 + 0.745934 0.000187 + 0.759893 0.000495 + 0.773849 0.000774 + 0.787811 0.001029 + 0.801751 0.001256 + 0.815687 0.001446 + 0.829631 0.001606 + 0.843542 0.001726 + 0.857468 0.001804 + 0.871383 0.001843 + 0.885282 0.001835 + 0.899161 0.001774 + 0.913026 0.001654 + 0.926888 0.001472 + 0.940732 0.001224 + 0.954588 0.000912 + 0.968372 0.000540 + 0.981788 0.000121 + 0.994042 -0.000302 + 1.000000 -0.000520 diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid44c.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid44c.dat new file mode 100644 index 00000000..66a8865f --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid44c.dat @@ -0,0 +1,161 @@ +MID 44c #Slobodan Midic, F5K-GPS Triangle (end of second panel) + 1.000000 0.000506 + 0.994120 0.000991 + 0.981841 0.002098 + 0.968638 0.003264 + 0.955045 0.004453 + 0.941394 0.005647 + 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-0.001649 + 0.988096 -0.001304 + 0.990823 -0.000997 + 0.993209 -0.000733 + 0.995246 -0.000509 + 0.996930 -0.000325 + 0.998256 -0.000182 + 0.999217 -0.000081 + 0.999802 -0.000020 + 1.000000 0.000000 + +MID 455 (c) is reflexed S type airfoil with pozitive +Cm for all AoA. It's suitable for human hang glider all kind. +Thikness is about 15%. Properties as in graph. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/mid97f.dat b/aerosandbox/geometry/airfoil/airfoil_database/mid97f.dat new file mode 100644 index 00000000..e81d6559 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/mid97f.dat @@ -0,0 +1,241 @@ +MID 97f #Slobodan Midic for F1A + 1.000000 0.002679 + 0.996220 0.003443 + 0.989444 0.004837 + 0.981504 0.006504 + 0.972803 0.008380 + 0.963598 0.010409 + 0.954124 0.012533 + 0.944521 0.014703 + 0.934894 0.016870 + 0.925310 0.018993 + 0.915741 0.021063 + 0.906186 0.023084 + 0.896652 0.025043 + 0.887077 0.026951 + 0.877466 0.028820 + 0.867861 0.030639 + 0.858218 0.032415 + 0.848543 0.034159 + 0.838880 0.035860 + 0.829233 0.037511 + 0.819554 0.039120 + 0.809855 0.040695 + 0.800216 0.042216 + 0.790581 0.043676 + 0.780896 0.045107 + 0.771310 0.046499 + 0.762101 0.047781 + 0.753318 0.048849 + 0.744717 0.049662 + 0.735963 0.050293 + 0.726836 0.050870 + 0.717324 0.051511 + 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b/aerosandbox/geometry/airfoil/airfoil_database/sb95_105_2.dat @@ -0,0 +1,62 @@ +SB95 10.5/2 (RCM 12/98) +1.000000 0.000068 +0.986237 0.001945 +0.951493 0.006731 +0.907474 0.013194 +0.861686 0.020272 +0.815417 0.027553 +0.769444 0.034674 +0.724023 0.041407 +0.678966 0.047594 +0.634168 0.053152 +0.589502 0.057995 +0.544724 0.062140 +0.500001 0.065577 +0.455431 0.068234 +0.411058 0.070074 +0.366938 0.070995 +0.323107 0.070929 +0.279646 0.069792 +0.236708 0.067493 +0.194531 0.063910 +0.153539 0.058902 +0.114422 0.052320 +0.078686 0.044171 +0.049507 0.035211 +0.029880 0.027248 +0.017959 0.020966 +0.010457 0.015890 +0.005499 0.011500 +0.002283 0.007414 +0.000504 0.003473 +0.000002 -0.000267 +0.000706 -0.003972 +0.002826 -0.007631 +0.006605 -0.010914 +0.012155 -0.013957 +0.020257 -0.017108 +0.032988 -0.020668 +0.054569 -0.024859 +0.087740 -0.029084 +0.127908 -0.032219 +0.170784 -0.034109 +0.214868 -0.034971 +0.259692 -0.035014 +0.304999 -0.034400 +0.350703 -0.033253 +0.396659 -0.031682 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index 00000000..a5501bbb --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sb95_95_2.dat @@ -0,0 +1,62 @@ +SB95 9.5/2 (RCM 12/98) +1.000000 -0.000039 +0.986293 0.001732 +0.951025 0.006338 +0.907744 0.012333 +0.863344 0.018788 +0.818582 0.025394 +0.774075 0.031860 +0.729973 0.038008 +0.686176 0.043693 +0.642570 0.048833 +0.599079 0.053354 +0.555535 0.057245 +0.511981 0.060512 +0.468531 0.063109 +0.425214 0.064982 +0.382077 0.066070 +0.339148 0.066303 +0.296484 0.065609 +0.254166 0.063909 +0.212366 0.061099 +0.171341 0.057049 +0.131538 0.051595 +0.093807 0.044575 +0.060202 0.036101 +0.035099 0.027536 +0.020038 0.020670 +0.011266 0.015407 +0.005806 0.011033 +0.002372 0.007046 +0.000499 0.003223 +0.000007 -0.000390 +0.000837 -0.003985 +0.003236 -0.007463 +0.007354 -0.010570 +0.013578 -0.013470 +0.023325 -0.016558 +0.040283 -0.020206 +0.069445 -0.024239 +0.107756 -0.027451 +0.149339 -0.029429 +0.192181 -0.030414 +0.235697 -0.030627 +0.279664 -0.030235 +0.323946 -0.029359 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b/aerosandbox/geometry/airfoil/airfoil_database/sb96_116_3.dat new file mode 100644 index 00000000..12dae49b --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sb96_116_3.dat @@ -0,0 +1,62 @@ +SB96 11.6/3.0 (RCM 12/98) +1.000000 0.001797 +0.986697 0.005909 +0.953898 0.013556 +0.912704 0.022021 +0.870049 0.030121 +0.827006 0.037809 +0.783790 0.045106 +0.740501 0.052027 +0.697246 0.058526 +0.654068 0.064551 +0.611163 0.069983 +0.568547 0.074635 +0.525829 0.078469 +0.482947 0.081555 +0.440106 0.083876 +0.397465 0.085369 +0.355199 0.085885 +0.313185 0.085301 +0.271553 0.083525 +0.230415 0.080417 +0.190004 0.075843 +0.150656 0.069609 +0.112974 0.061527 +0.077982 0.051440 +0.047823 0.039663 +0.026233 0.028176 +0.013889 0.019335 +0.007053 0.012908 +0.003036 0.008009 +0.000786 0.003885 +0.000012 0.000204 +0.000810 -0.003344 +0.003466 -0.006790 +0.008012 -0.010137 +0.015213 -0.013731 +0.027525 -0.017948 +0.050073 -0.022976 +0.084065 -0.027570 +0.123400 -0.030491 +0.164784 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--git a/aerosandbox/geometry/airfoil/airfoil_database/sb96_lm.dat b/aerosandbox/geometry/airfoil/airfoil_database/sb96_lm.dat new file mode 100644 index 00000000..0b0ea38e --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sb96_lm.dat @@ -0,0 +1,62 @@ +SB96 LM 8/3.0 (RCM 12/98) +1.000000 0.000000 +0.992507 0.003210 +0.972684 0.007768 +0.937011 0.014832 +0.896682 0.021833 +0.855536 0.028245 +0.814127 0.034147 +0.772568 0.039573 +0.730873 0.044564 +0.689062 0.049151 +0.647158 0.053370 +0.605255 0.057219 +0.563414 0.060646 +0.521543 0.063635 +0.479731 0.066169 +0.438077 0.068138 +0.396603 0.069531 +0.355311 0.070162 +0.314236 0.069963 +0.273447 0.068823 +0.233042 0.066608 +0.193157 0.063159 +0.154005 0.058288 +0.115988 0.051769 +0.079808 0.043328 +0.047232 0.032897 +0.022911 0.021891 +0.010232 0.013725 +0.004204 0.008292 +0.001163 0.004145 +0.000026 0.000565 +0.000650 -0.002770 +0.003397 -0.005756 +0.008514 -0.008042 +0.017791 -0.009930 +0.038355 -0.011739 +0.074893 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00000000..384fdd0e --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sb98vs5.dat @@ -0,0 +1,63 @@ +SB 98 VS5 (Looping 01/2000) +1.000000 0.000201 +0.986678 0.003320 +0.952184 0.009673 +0.912142 0.016138 +0.871355 0.022189 +0.830284 0.027914 +0.789039 0.033387 +0.747704 0.038650 +0.706407 0.043689 +0.665226 0.048431 +0.624126 0.052801 +0.582963 0.056790 +0.541894 0.060385 +0.501095 0.063427 +0.460268 0.065854 +0.419438 0.067691 +0.379126 0.068787 +0.339144 0.068836 +0.299075 0.067853 +0.259193 0.065868 +0.220252 0.062678 +0.181698 0.057297 +0.143183 0.051610 +0.105378 0.043790 +0.068011 0.034496 +0.036012 0.024544 +0.016543 0.016289 +0.007418 0.010767 +0.002808 0.006527 +0.000538 0.002766 +0.000034 -0.000647 +0.001340 -0.004026 +0.004756 -0.007197 +0.010988 -0.010185 +0.023268 -0.013714 +0.049354 -0.018282 +0.086535 -0.022438 +0.125994 -0.025388 +0.166623 -0.027541 +0.207666 -0.029106 +0.248962 -0.030237 +0.290124 -0.030956 +0.331177 -0.031157 +0.372334 -0.030853 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a/aerosandbox/geometry/airfoil/airfoil_database/sb99a22c4.dat b/aerosandbox/geometry/airfoil/airfoil_database/sb99a22c4.dat new file mode 100644 index 00000000..a85da10e --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sb99a22c4.dat @@ -0,0 +1,62 @@ +ASW-7.33m de MCM (RCM août 2001) +1.000000 0.001665 +0.984752 0.004825 +0.950231 0.011955 +0.903361 0.021946 +0.852811 0.032350 +0.801415 0.042344 +0.749835 0.051882 +0.698485 0.060824 +0.647293 0.069092 +0.596211 0.076653 +0.545303 0.083470 +0.495263 0.089353 +0.446216 0.094018 +0.398096 0.097288 +0.350854 0.098984 +0.304261 0.099009 +0.258817 0.097291 +0.215147 0.093700 +0.173803 0.088069 +0.135362 0.080379 +0.100965 0.070918 +0.072330 0.060578 +0.050610 0.050602 +0.035047 0.041696 +0.023986 0.033977 +0.016011 0.027250 +0.010175 0.021269 +0.005910 0.015830 +0.002893 0.010783 +0.000972 0.006030 +0.000087 0.001551 +0.000223 -0.002722 +0.001540 -0.007039 +0.004223 -0.011163 +0.008278 -0.014891 +0.013706 -0.018213 +0.020708 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barreau" 20/12/03 \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/sb99blkr.dat b/aerosandbox/geometry/airfoil/airfoil_database/sb99blkr.dat new file mode 100644 index 00000000..8d9a168c --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sb99blkr.dat @@ -0,0 +1,63 @@ +SB99blkr Emplanture blanick Aerotech +1.000000 0.001453 +0.985959 0.003478 +0.950674 0.008544 +0.906770 0.015143 +0.861956 0.021668 +0.816872 0.027908 +0.771651 0.033938 +0.722664 0.039675 +0.681694 0.045046 +0.636815 0.050031 +0.592059 0.054577 +0.547398 0.058624 +0.502747 0.062151 +0.458229 0.065131 +0.414063 0.067446 +0.370237 0.068963 +0.326740 0.069585 +0.283763 0.069179 +0.241394 0.067585 +0.199749 0.064634 +0.159006 0.060181 +0.119797 0.054087 +0.083420 0.046284 +0.052822 0.037280 +0.031438 0.028628 +0.018434 0.021582 +0.010520 0.015976 +0.005470 0.011257 +0.002254 0.007039 +0.000481 0.003101 +0.000029 -0.000576 +0.000905 -0.004235 +0.003341 -0.007796 +0.007429 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+0.981678 0.000318 +1.000000 0.000060 + +"gerard barreau" 20/12/03 \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/sb99f3j.dat b/aerosandbox/geometry/airfoil/airfoil_database/sb99f3j.dat new file mode 100644 index 00000000..83b93f65 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sb99f3j.dat @@ -0,0 +1,62 @@ +SB 99 F3J (Looping 01/2000) +1.000000 0.001378 +0.986282 0.004081 +0.950653 0.010926 +0.908773 0.019194 +0.867250 0.026890 +0.825427 0.033840 +0.782901 0.040405 +0.740409 0.046562 +0.697956 0.052231 +0.655384 0.057436 +0.612751 0.062186 +0.570104 0.066473 +0.527455 0.070273 +0.484843 0.073567 +0.442486 0.076275 +0.400539 0.078219 +0.358854 0.079258 +0.317482 0.079295 +0.276596 0.078178 +0.236248 0.075746 +0.196504 0.071832 +0.157464 0.066310 +0.119657 0.059060 +0.083937 0.049948 +0.052337 0.039173 +0.028693 0.028106 +0.014830 0.019249 +0.007377 0.012862 +0.003153 0.007961 +0.000833 0.003835 +0.000021 0.000168 +0.000709 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+ 0.861000 0.031154 + 0.814614 0.038814 + 0.767772 0.046139 + 0.721149 0.052992 + 0.674574 0.059306 + 0.628001 0.065083 + 0.581531 0.070272 + 0.535133 0.074823 + 0.488806 0.078714 + 0.442850 0.081864 + 0.397520 0.084075 + 0.352684 0.085192 + 0.308468 0.085094 + 0.265078 0.083604 + 0.222633 0.080546 + 0.181225 0.075753 + 0.141308 0.069144 + 0.103939 0.060708 + 0.071116 0.050804 + 0.045758 0.040658 + 0.028640 0.031656 + 0.017686 0.024291 + 0.010545 0.018235 + 0.005760 0.013052 + 0.002581 0.008435 + 0.000702 0.004179 + 0.000022 0.000229 + 0.000527 -0.003603 + 0.002479 -0.007389 + 0.005993 -0.010806 + 0.011125 -0.013813 + 0.018292 -0.016629 + 0.028709 -0.019504 + 0.045088 -0.022579 + 0.071757 -0.025662 + 0.109448 -0.027957 + 0.152959 -0.029030 + 0.198721 -0.029110 + 0.245694 -0.028519 + 0.293274 -0.027513 + 0.341148 -0.026209 + 0.389186 -0.024676 + 0.437286 -0.022964 + 0.485096 -0.021055 + 0.532657 -0.018838 + 0.580111 -0.016252 + 0.627845 -0.013297 + 0.676007 -0.010157 + 0.723815 -0.007173 + 0.771125 -0.004553 + 0.817920 -0.002430 + 0.862851 -0.001088 + 0.906989 -0.001232 + 0.951031 -0.002405 + 0.985688 -0.003690 + 1.000000 -0.004349 + +Serge Barth nous a developpe ce profil un peut special pour avion electrique +ou planeur (en l'amincissant). + +Pour certain constructeur a la recherche de modeles vite construit et leger +sur la base d'ailes en polystyrene voici un profil a essayer. + +Il est prevue pour des ailes non coffre ou tout juste avec du papier ou +vinyle. +Pour cela mecaniquement son BF est epais, il ne fini pas a zero pour pouvoir +rester brut de decoupe en poly. diff --git a/aerosandbox/geometry/airfoil/airfoil_database/sc17.dat b/aerosandbox/geometry/airfoil/airfoil_database/sc17.dat new file mode 100644 index 00000000..2df1c193 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sc17.dat @@ -0,0 +1,84 @@ +SC17 profil voltige (c)Stephane Combet +1.00000 0.00000 +0.98741 0.00146 +0.95861 0.00432 +0.92583 0.00729 +0.89171 0.01034 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-0.0346 +0.50842 -0.03271 +0.54232 -0.03065 +0.57628 -0.02845 +0.61022 -0.02613 +0.64436 -0.0237 +0.67847 -0.02123 +0.71266 -0.0187 +0.74687 -0.01618 +0.78103 -0.01371 +0.81520 -0.01128 +0.84916 -0.00894 +0.88317 -0.00671 +0.91681 -0.00464 +0.94989 -0.00272 +0.97604 -0.00137 +0.98799 -0.00082 +1.00000 0.00000 + +https://voltige-planeur-rc.net/2018/09/05/sc17-an-aerobatic-airfoil-proposal/ +https://www.youtube.com/channel/UCocDAjUfuTzs6sudO2wxQgQ/videos - https://velivoltige.com/ \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/sc17s.dat b/aerosandbox/geometry/airfoil/airfoil_database/sc17s.dat new file mode 100644 index 00000000..8c8f7af8 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/sc17s.dat @@ -0,0 +1,85 @@ +SC17s profil voltige Stephane Combet +1.00000 0.00000 +0.97122 0.00303 +0.92507 0.00718 +0.87684 0.01132 +0.82761 0.01551 +0.77799 0.01971 +0.72827 0.02387 +0.67860 0.02796 +0.62905 0.03188 +0.57956 0.03561 +0.53025 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a/aerosandbox/geometry/airfoil/airfoil_database/tp28-0.dat b/aerosandbox/geometry/airfoil/airfoil_database/tp28-0.dat new file mode 100644 index 00000000..263a0801 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp28-0.dat @@ -0,0 +1,261 @@ +TP28-0% opt-26 Voltige (c)Th Platon + 1.00000 0.00014 + 0.99597 0.00032 + 0.98907 0.00064 + 0.98109 0.00104 + 0.96469 0.00188 + 0.95644 0.00233 + 0.94798 0.00279 + 0.93963 0.00328 + 0.93136 0.00376 + 0.92307 0.00427 + 0.91470 0.00478 + 0.90625 0.00532 + 0.89772 0.00588 + 0.88921 0.00644 + 0.88070 0.00702 + 0.87219 0.00760 + 0.86365 0.00820 + 0.85513 0.00881 + 0.84662 0.00942 + 0.83812 0.01005 + 0.82962 0.01068 + 0.82111 0.01132 + 0.81260 0.01197 + 0.80408 0.01263 + 0.79555 0.01328 + 0.78702 0.01395 + 0.77849 0.01463 + 0.76996 0.01531 + 0.76143 0.01599 + 0.75290 0.01668 + 0.74437 0.01736 + 0.73584 0.01805 + 0.72731 0.01874 + 0.71878 0.01944 + 0.71025 0.02013 + 0.70172 0.02083 + 0.69318 0.02153 + 0.68464 0.02223 + 0.67611 0.02293 + 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0.98109 -0.00104 + 0.98907 -0.00064 + 0.99597 -0.00032 + 1.00000 -0.00014 +http://pierre.rondel.free.fr/images2/choix_voltige/ + TP28-opt-0.66% est un profil à faible courbure, doté d'un excellent Cx min à RE:200.000 il est tout particulièrement destiné à des petits planeurs de moins de 2m50 d'envergure qui avec une charge alaire allant jusqu'à 45g/dm² passeront aussi bien la boucle carrée dos que le Voltij tout en étant plus rapide et en grattant nettement mieux dans le petit temps. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/tp28-4.dat b/aerosandbox/geometry/airfoil/airfoil_database/tp28-4.dat new file mode 100644 index 00000000..105feb44 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp28-4.dat @@ -0,0 +1,260 @@ +TP28-4 Voltige (c)Th Platon + 1.00000 0.00007 + 0.99597 0.00045 + 0.98907 0.00117 + 0.98109 0.00206 + 0.96469 0.00390 + 0.95644 0.00482 + 0.94798 0.00576 + 0.93963 0.00666 + 0.93136 0.00756 + 0.92307 0.00845 + 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Accélérant presque autant que Ritz 1.30.10, il devrait permettre la réalisation de planeurs "voltige totale" ayant, une certaine polyvalence pente et plaine (en fonction du ballast), un planeur de 3m50 d'envergure devrait passer la boucle carrée dos jusqu'à 60 à 65 g/dm² et gratter correctement (en tout cas au moins aussi bien qu'un Ritz1.30.10) surtout si on l'allège un peu. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/tp28-60.dat b/aerosandbox/geometry/airfoil/airfoil_database/tp28-60.dat new file mode 100644 index 00000000..ef3f4a2a --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp28-60.dat @@ -0,0 +1,261 @@ +TP28-60 Voltige (c)Th Platon + 1.00000 0.00007 + 0.99597 0.00030 + 0.98907 0.00074 + 0.98109 0.00130 + 0.96469 0.00256 + 0.95644 0.00325 + 0.94798 0.00398 + 0.93963 0.00472 + 0.93136 0.00548 + 0.92307 0.00625 + 0.91470 0.00705 + 0.90625 0.00786 + 0.89772 0.00870 + 0.88921 0.00955 + 0.88070 0.01040 + 0.87219 0.01127 + 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0.78702 -0.01088 + 0.79555 -0.01032 + 0.80408 -0.00975 + 0.81260 -0.00921 + 0.82111 -0.00866 + 0.82962 -0.00812 + 0.83812 -0.00758 + 0.84662 -0.00707 + 0.85513 -0.00655 + 0.86365 -0.00604 + 0.87219 -0.00554 + 0.88070 -0.00505 + 0.88921 -0.00458 + 0.89772 -0.00412 + 0.90625 -0.00366 + 0.91470 -0.00324 + 0.92307 -0.00282 + 0.93136 -0.00244 + 0.93963 -0.00206 + 0.94797 -0.00170 + 0.95644 -0.00136 + 0.96469 -0.00105 + 0.98109 -0.00051 + 0.98907 -0.00029 + 0.99597 -0.00014 + 1.00000 -0.00007 +http://pierre.rondel.free.fr/images2/choix_voltige/ +TP28-60 gratte encore mieux (aussi bien que Ritz 1.30.10 tout en étant bien meilleur sur le dos), il "aime bien" les Reynolds un peu élevés mais son épaisseur un peu faible limite son utilisation à des envergures nettement inférieures à 3m. Je ne suis pas sûr que ce profil ait véritablement un avenir. \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/tp28-l.dat b/aerosandbox/geometry/airfoil/airfoil_database/tp28-l.dat new file mode 100644 index 00000000..8f368ae8 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp28-l.dat @@ -0,0 +1,260 @@ +TP28-L Voltige SYMETRIX (c)Th Platon + 1.00000 0.00007 + 0.99597 0.00032 + 0.98907 0.00082 + 0.98109 0.00148 + 0.96469 0.00294 + 0.95644 0.00367 + 0.94798 0.00440 + 0.93963 0.00511 + 0.93136 0.00580 + 0.92307 0.00648 + 0.91470 0.00717 + 0.90625 0.00786 + 0.89772 0.00856 + 0.88921 0.00926 + 0.88070 0.00996 + 0.87219 0.01066 + 0.86365 0.01137 + 0.85513 0.01208 + 0.84662 0.01278 + 0.83812 0.01350 + 0.82962 0.01422 + 0.82111 0.01494 + 0.81260 0.01566 + 0.80408 0.01639 + 0.79555 0.01712 + 0.78702 0.01784 + 0.77849 0.01857 + 0.76996 0.01930 + 0.76143 0.02003 + 0.75290 0.02076 + 0.74437 0.02149 + 0.73584 0.02221 + 0.72731 0.02294 + 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TP28-L est le profil que j'ai retenu pour mon futur planeur de voltige en plaine, il aime les Reynolds élevés et est donc bien adapté aux grands planeurs jusqu'à près de 4m et 75g/dm²(en construisant solide!) TP 28-opt est lui, de par son épaisseur, plutôt destiné à des planeurs de moins de 2m80 d'envergure. Ce sont tous deux des alternatives intéressantes à MG05. Pour les Re supérieurs à 200.000 leurs polaires sont en tout point du domaine meilleures que celle de MG05! TP28-opt pourra notamment être utilisé à l'emplanture d'un planeur de la taille du Voltij , au saumon on aura par contre intérêt à conserver MG05 qui donne d'excellent résultat à faible Reynolds.ou encore TPS004 8.2%-0% si on veut améliorer les figures déclenchées. diff --git a/aerosandbox/geometry/airfoil/airfoil_database/tp28-m.dat b/aerosandbox/geometry/airfoil/airfoil_database/tp28-m.dat new file mode 100644 index 00000000..ff7c2a8c --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp28-m.dat @@ -0,0 +1,259 @@ +TP28-milieu (c)Th Platon + 1.00000 0.00004 + 0.99597 0.00026 + 0.98907 0.00066 + 0.98109 0.00118 + 0.96469 0.00228 + 0.95644 0.00282 + 0.94798 0.00337 + 0.93963 0.00393 + 0.93136 0.00447 + 0.92307 0.00502 + 0.91470 0.00557 + 0.90625 0.00612 + 0.89772 0.00667 + 0.88921 0.00722 + 0.88070 0.00778 + 0.87219 0.00832 + 0.86365 0.00888 + 0.85513 0.00945 + 0.84662 0.01001 + 0.83812 0.01061 + 0.82962 0.01119 + 0.82111 0.01179 + 0.81260 0.01240 + 0.80408 0.01300 + 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de 4m) , 8% (F3B/F3F/F3J) +et pouvant descendre jusqu' 5% (DLG) - profil de saumon associé à TP42 (épaisseur entre 9 et 8%) \ No newline at end of file diff --git a/aerosandbox/geometry/airfoil/airfoil_database/tp29-7.dat b/aerosandbox/geometry/airfoil/airfoil_database/tp29-7.dat new file mode 100644 index 00000000..2626b1ec --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp29-7.dat @@ -0,0 +1,264 @@ +TP29-7% Profil de stab (c)Th Platon + 1.00000 0.00043 + 0.99561 0.00059 + 0.98788 0.00089 + 0.97978 0.00121 + 0.97162 0.00153 + 0.96344 0.00186 + 0.95527 0.00219 + 0.94710 0.00253 + 0.93893 0.00288 + 0.93075 0.00324 + 0.92257 0.00360 + 0.91439 0.00397 + 0.90620 0.00434 + 0.89802 0.00471 + 0.88985 0.00509 + 0.88168 0.00547 + 0.87350 0.00586 + 0.86532 0.00626 + 0.85715 0.00665 + 0.84898 0.00705 + 0.84082 0.00745 + 0.83267 0.00785 + 0.82452 0.00826 + 0.81634 0.00868 + 0.80816 0.00909 + 0.79998 0.00950 + 0.79181 0.00993 + 0.78364 0.01035 + 0.77549 0.01077 + 0.76734 0.01119 + 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index 00000000..a59b8a05 --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp29-85.dat @@ -0,0 +1,262 @@ +TP29-1-8.5% MU28 Ph Jambon saumon du (c)Th Platon + 1.00000 0.00053 + 0.99625 0.00069 + 0.98983 0.00099 + 0.98248 0.00133 + 0.97435 0.00172 + 0.96572 0.00215 + 0.95681 0.00259 + 0.94775 0.00305 + 0.93860 0.00352 + 0.92941 0.00400 + 0.92017 0.00450 + 0.91091 0.00501 + 0.90165 0.00552 + 0.89242 0.00604 + 0.88320 0.00656 + 0.87397 0.00709 + 0.86477 0.00763 + 0.85557 0.00817 + 0.84635 0.00872 + 0.83714 0.00926 + 0.82794 0.00983 + 0.81871 0.01039 + 0.80951 0.01096 + 0.80033 0.01152 + 0.79117 0.01210 + 0.78202 0.01266 + 0.77286 0.01324 + 0.76367 0.01382 + 0.75446 0.01441 + 0.74522 0.01501 + 0.73599 0.01559 + 0.72676 0.01618 + 0.71753 0.01678 + 0.70829 0.01739 + 0.69906 0.01800 + 0.68981 0.01860 + 0.68055 0.01921 + 0.67129 0.01981 + 0.66202 0.02043 + 0.65274 0.02104 + 0.64344 0.02166 + 0.63415 0.02228 + 0.62487 0.02290 + 0.61562 0.02351 + 0.60636 0.02412 + 0.59711 0.02473 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a/aerosandbox/geometry/airfoil/airfoil_database/tp29-9.dat b/aerosandbox/geometry/airfoil/airfoil_database/tp29-9.dat new file mode 100644 index 00000000..87ab966e --- /dev/null +++ b/aerosandbox/geometry/airfoil/airfoil_database/tp29-9.dat @@ -0,0 +1,264 @@ +TP29-9% Saumon du Wasabi et Profil de stab (c)Th Platon + 1.00000 0.00056 + 0.99539 0.00077 + 0.98772 0.00115 + 0.97951 0.00157 + 0.97107 0.00200 + 0.96258 0.00243 + 0.95407 0.00288 + 0.94556 0.00334 + 0.93703 0.00381 + 0.92850 0.00429 + 0.91996 0.00478 + 0.91142 0.00528 + 0.90287 0.00577 + 0.89434 0.00627 + 0.88581 0.00678 + 0.87729 0.00730 + 0.86876 0.00783 + 0.86023 0.00836 + 0.85171 0.00889 + 0.84321 0.00943 + 0.83472 0.00996 + 0.82623 0.01051 + 0.81771 0.01107 + 0.80919 0.01162 + 0.80066 0.01218 + 0.79215 0.01274 + 0.78363 0.01331 + 0.77512 0.01387 + 0.76662 0.01443 + 0.75810 0.01501 + 0.74958 0.01558 + 0.74107 0.01617 + 0.73257 0.01675 + 0.72408 0.01732 + 0.71557 0.01791 + 0.70707 0.01850 + 0.69858 0.01909 + 0.69009 0.01968 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