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EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 422 AIRFOIL (e422-il)
Reynolds number: 500,000
Max Cl/Cd: 105.84 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e422-il-500000.txt
Download as CSV file: xf-e422-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 422 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0323   0.10070   0.09707  -0.0880   0.6999   0.0213
 -10.000   0.0376   0.09800   0.09430  -0.0889   0.6857   0.0218
  -9.500   0.0349   0.09086   0.08709  -0.0928   0.6640   0.0225
  -9.250   0.0457   0.08886   0.08503  -0.0926   0.6519   0.0227
  -8.750   0.0663   0.08503   0.08111  -0.0928   0.6301   0.0233
  -8.250   0.0798   0.08041   0.07643  -0.0940   0.6131   0.0243
  -8.000   0.0853   0.07801   0.07401  -0.0948   0.6055   0.0247
  -7.750   0.0692   0.07234   0.06837  -0.0989   0.6018   0.0261
  -7.500   0.0724   0.06955   0.06560  -0.0993   0.5950   0.0263
  -7.250   0.0818   0.06809   0.06410  -0.0987   0.5874   0.0265
  -7.000   0.0885   0.06639   0.06239  -0.0985   0.5810   0.0268
  -6.750   0.0916   0.06461   0.06062  -0.0983   0.5746   0.0271
  -6.500   0.0970   0.06244   0.05842  -0.0992   0.5687   0.0277
  -6.250   0.0285   0.02412   0.01871  -0.1306   0.5773   0.0158
  -6.000   0.0472   0.02179   0.01606  -0.1303   0.5708   0.0154
  -5.750   0.0680   0.01986   0.01376  -0.1298   0.5647   0.0151
  -5.500   0.0909   0.01832   0.01192  -0.1292   0.5586   0.0148
  -5.250   0.1147   0.01718   0.01051  -0.1285   0.5526   0.0147
  -5.000   0.1393   0.01629   0.00938  -0.1279   0.5471   0.0148
  -4.750   0.1650   0.01552   0.00847  -0.1273   0.5419   0.0150
  -4.500   0.1908   0.01491   0.00770  -0.1268   0.5366   0.0154
  -4.250   0.2167   0.01446   0.00709  -0.1262   0.5315   0.0158
  -4.000   0.2423   0.01379   0.00636  -0.1257   0.5268   0.0165
  -3.750   0.2688   0.01339   0.00593  -0.1253   0.5219   0.0174
  -3.500   0.2955   0.01308   0.00552  -0.1249   0.5173   0.0184
  -3.250   0.3219   0.01277   0.00510  -0.1244   0.5128   0.0196
  -3.000   0.3492   0.01247   0.00479  -0.1241   0.5092   0.0214
  -2.750   0.3764   0.01217   0.00445  -0.1238   0.5053   0.0244
  -2.500   0.4034   0.01189   0.00414  -0.1234   0.5013   0.0321
  -2.250   0.4296   0.01141   0.00380  -0.1230   0.4975   0.0756
  -2.000   0.4567   0.01132   0.00377  -0.1227   0.4937   0.1079
  -1.750   0.4843   0.01125   0.00377  -0.1225   0.4903   0.1282
  -1.500   0.5119   0.01125   0.00378  -0.1223   0.4869   0.1444
  -1.250   0.5395   0.01128   0.00379  -0.1221   0.4836   0.1579
  -1.000   0.5670   0.01137   0.00383  -0.1218   0.4804   0.1710
  -0.750   0.5945   0.01147   0.00390  -0.1216   0.4769   0.1826
  -0.500   0.6220   0.01143   0.00389  -0.1214   0.4742   0.1930
  -0.250   0.6495   0.01146   0.00390  -0.1211   0.4711   0.2028
   0.000   0.6767   0.01143   0.00389  -0.1209   0.4681   0.2125
   0.250   0.7041   0.01148   0.00390  -0.1206   0.4654   0.2221
   0.500   0.7312   0.01152   0.00392  -0.1204   0.4626   0.2328
   0.750   0.7587   0.01165   0.00400  -0.1202   0.4596   0.2435
   1.000   0.7856   0.01162   0.00404  -0.1199   0.4573   0.2565
   1.250   0.8126   0.01161   0.00408  -0.1197   0.4546   0.2708
   1.500   0.8395   0.01162   0.00414  -0.1194   0.4518   0.2882
   1.750   0.8664   0.01165   0.00420  -0.1191   0.4493   0.3105
   2.000   0.8931   0.01168   0.00429  -0.1189   0.4468   0.3407
   2.250   0.9198   0.01176   0.00443  -0.1187   0.4441   0.3849
   2.500   0.9458   0.01172   0.00460  -0.1184   0.4418   0.4635
   2.750   0.9950   0.01083   0.00481  -0.1230   0.4391   1.0000
   3.000   1.0208   0.01095   0.00489  -0.1225   0.4366   1.0000
   3.250   1.0467   0.01108   0.00498  -0.1220   0.4341   1.0000
   3.500   1.0725   0.01122   0.00508  -0.1216   0.4319   1.0000
   3.750   1.0984   0.01139   0.00520  -0.1212   0.4296   1.0000
   4.000   1.1247   0.01165   0.00538  -0.1209   0.4269   1.0000
   4.250   1.1503   0.01182   0.00555  -0.1205   0.4247   1.0000
   4.500   1.1754   0.01193   0.00569  -0.1199   0.4225   1.0000
   4.750   1.2007   0.01207   0.00583  -0.1194   0.4202   1.0000
   5.000   1.2261   0.01223   0.00598  -0.1190   0.4179   1.0000
   5.250   1.2513   0.01238   0.00612  -0.1185   0.4156   1.0000
   5.500   1.2766   0.01255   0.00627  -0.1181   0.4132   1.0000
   5.750   1.3025   0.01282   0.00649  -0.1178   0.4106   1.0000
   6.000   1.3277   0.01305   0.00673  -0.1174   0.4084   1.0000
   6.250   1.3517   0.01319   0.00692  -0.1167   0.4062   1.0000
   6.500   1.3758   0.01334   0.00710  -0.1161   0.4037   1.0000
   6.750   1.4000   0.01349   0.00727  -0.1155   0.4011   1.0000
   7.000   1.4242   0.01365   0.00744  -0.1150   0.3986   1.0000
   7.250   1.4484   0.01385   0.00761  -0.1144   0.3959   1.0000
   7.500   1.4735   0.01417   0.00790  -0.1141   0.3927   1.0000
   7.750   1.4951   0.01427   0.00810  -0.1131   0.3902   1.0000
   8.000   1.5175   0.01443   0.00830  -0.1122   0.3874   1.0000
   8.250   1.5400   0.01459   0.00850  -0.1114   0.3845   1.0000
   8.500   1.5622   0.01476   0.00869  -0.1105   0.3817   1.0000
   8.750   1.5852   0.01501   0.00891  -0.1098   0.3787   1.0000
   9.000   1.6070   0.01527   0.00921  -0.1090   0.3758   1.0000
   9.250   1.6263   0.01543   0.00946  -0.1076   0.3727   1.0000
   9.500   1.6458   0.01560   0.00968  -0.1063   0.3694   1.0000
   9.750   1.6644   0.01578   0.00990  -0.1048   0.3662   1.0000
  10.000   1.6831   0.01605   0.01015  -0.1034   0.3629   1.0000
  10.250   1.7000   0.01632   0.01048  -0.1017   0.3598   1.0000
  10.500   1.7144   0.01654   0.01079  -0.0996   0.3563   1.0000
  10.750   1.7298   0.01679   0.01111  -0.0977   0.3527   1.0000
  11.000   1.7451   0.01709   0.01142  -0.0959   0.3492   1.0000
  11.250   1.7605   0.01748   0.01182  -0.0941   0.3453   1.0000
  11.500   1.7735   0.01781   0.01227  -0.0920   0.3412   1.0000
  11.750   1.7869   0.01819   0.01272  -0.0901   0.3369   1.0000
  12.000   1.7989   0.01869   0.01322  -0.0881   0.3327   1.0000
  12.250   1.8108   0.01921   0.01383  -0.0862   0.3281   1.0000
  12.500   1.8221   0.01978   0.01448  -0.0843   0.3230   1.0000
  12.750   1.8303   0.02053   0.01524  -0.0821   0.3179   1.0000
  13.000   1.8399   0.02130   0.01610  -0.0803   0.3125   1.0000
  13.250   1.8477   0.02221   0.01707  -0.0784   0.3065   1.0000
  13.500   1.8519   0.02340   0.01828  -0.0763   0.3009   1.0000
  13.750   1.8590   0.02454   0.01952  -0.0748   0.2941   1.0000
  14.000   1.8590   0.02620   0.02118  -0.0728   0.2873   1.0000
  14.250   1.8633   0.02771   0.02279  -0.0714   0.2800   1.0000
  14.500   1.8586   0.02997   0.02505  -0.0696   0.2722   1.0000
  14.750   1.8575   0.03212   0.02728  -0.0684   0.2635   1.0000
  15.000   1.8503   0.03488   0.03007  -0.0670   0.2553   1.0000
  15.250   1.8398   0.03810   0.03332  -0.0658   0.2462   1.0000
  15.500   1.8301   0.04139   0.03666  -0.0648   0.2374   1.0000
  15.750   1.8132   0.04550   0.04078  -0.0639   0.2285   1.0000
  16.000   1.7985   0.04959   0.04492  -0.0633   0.2198   1.0000
  16.250   1.7830   0.05389   0.04925  -0.0629   0.2116   1.0000
  16.500   1.7631   0.05883   0.05419  -0.0626   0.2035   1.0000
  16.750   1.7504   0.06310   0.05852  -0.0626   0.1955   1.0000
  17.000   1.7314   0.06820   0.06362  -0.0628   0.1883   1.0000
  17.250   1.7197   0.07256   0.06804  -0.0630   0.1808   1.0000
  17.500   1.7037   0.07753   0.07302  -0.0635   0.1740   1.0000
  17.750   1.6924   0.08202   0.07755  -0.0640   0.1670   1.0000
  18.000   1.6796   0.08675   0.08230  -0.0647   0.1608   1.0000
  18.250   1.6708   0.09106   0.08665  -0.0655   0.1540   1.0000
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