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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 100,000
Max Cl/Cd: 46.24 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e431-il-100000-n5.txt
Download as CSV file: xf-e431-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 431 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1790   0.09570   0.09074  -0.0905   0.9463   0.0219
  -9.750  -0.1732   0.09082   0.08587  -0.0943   0.9397   0.0214
  -9.250  -0.1697   0.07620   0.07126  -0.1077   0.9278   0.0190
  -9.000  -0.1677   0.07008   0.06512  -0.1138   0.9197   0.0187
  -8.750  -0.1696   0.06375   0.05869  -0.1204   0.9120   0.0184
  -8.500  -0.1799   0.05863   0.05343  -0.1241   0.9018   0.0182
  -8.250  -0.1928   0.05506   0.04970  -0.1243   0.8908   0.0179
  -8.000  -0.1965   0.05079   0.04515  -0.1255   0.8840   0.0177
  -7.750  -0.2043   0.04779   0.04191  -0.1236   0.8742   0.0175
  -7.500  -0.2009   0.04396   0.03767  -0.1234   0.8685   0.0175
  -7.250  -0.2006   0.04134   0.03471  -0.1211   0.8604   0.0176
  -7.000  -0.1922   0.03809   0.03092  -0.1199   0.8547   0.0185
  -6.750  -0.1741   0.03495   0.02717  -0.1197   0.8513   0.0189
  -6.500  -0.1659   0.03362   0.02562  -0.1172   0.8436   0.0197
  -6.250  -0.1444   0.03221   0.02400  -0.1170   0.8393   0.0210
  -6.000  -0.1185   0.03005   0.02142  -0.1171   0.8363   0.0216
  -5.750  -0.1007   0.02863   0.01970  -0.1155   0.8309   0.0221
  -5.500  -0.0796   0.02723   0.01800  -0.1142   0.8260   0.0229
  -5.250  -0.0533   0.02597   0.01662  -0.1141   0.8225   0.0241
  -5.000  -0.0245   0.02488   0.01541  -0.1145   0.8198   0.0262
  -4.750  -0.0087   0.02434   0.01481  -0.1125   0.8141   0.0292
  -4.500   0.0122   0.02373   0.01411  -0.1115   0.8094   0.0327
  -4.250   0.0376   0.02288   0.01323  -0.1113   0.8060   0.0375
  -4.000   0.0661   0.02210   0.01239  -0.1116   0.8034   0.0476
  -3.750   0.0790   0.02176   0.01213  -0.1092   0.7972   0.0601
  -3.500   0.1001   0.02117   0.01166  -0.1083   0.7928   0.0918
  -3.250   0.1249   0.02029   0.01119  -0.1083   0.7895   0.1693
  -3.000   0.1483   0.01888   0.01071  -0.1086   0.7870   0.3808
  -2.750   0.1462   0.01880   0.01174  -0.1021   0.7800   0.6074
  -2.500   0.1654   0.01923   0.01216  -0.0994   0.7759   0.7025
  -2.250   0.1913   0.01955   0.01229  -0.0982   0.7729   0.7461
  -2.000   0.2162   0.01985   0.01245  -0.0964   0.7706   0.7719
  -1.750   0.2200   0.02043   0.01299  -0.0917   0.7629   0.7888
  -1.500   0.2379   0.02072   0.01318  -0.0889   0.7589   0.8118
  -1.250   0.2550   0.02095   0.01334  -0.0850   0.7561   0.8346
  -1.000   0.2619   0.02128   0.01363  -0.0803   0.7506   0.8532
  -0.750   0.2749   0.02145   0.01372  -0.0774   0.7450   0.8642
  -0.500   0.3031   0.02136   0.01348  -0.0775   0.7418   0.8702
  -0.250   0.3361   0.02122   0.01318  -0.0787   0.7395   0.8749
   0.000   0.3435   0.02153   0.01347  -0.0754   0.7324   0.8802
   0.250   0.3670   0.02156   0.01340  -0.0749   0.7279   0.8849
   0.500   0.3989   0.02146   0.01318  -0.0760   0.7250   0.8886
   0.750   0.4343   0.02128   0.01289  -0.0775   0.7229   0.8913
   1.000   0.4354   0.02177   0.01341  -0.0733   0.7141   0.8970
   1.250   0.4645   0.02172   0.01328  -0.0739   0.7105   0.9008
   1.500   0.4994   0.02157   0.01304  -0.0754   0.7080   0.9040
   1.750   0.5088   0.02194   0.01343  -0.0726   0.7007   0.9089
   2.000   0.5328   0.02201   0.01346  -0.0723   0.6957   0.9129
   2.250   0.5670   0.02185   0.01325  -0.0736   0.6928   0.9164
   2.750   0.6025   0.02227   0.01369  -0.0710   0.6805   0.9266
   3.000   0.6376   0.02210   0.01349  -0.0724   0.6773   0.9298
   3.250   0.6770   0.02183   0.01318  -0.0745   0.6749   0.9328
   3.500   0.6751   0.02248   0.01393  -0.0701   0.6647   0.9420
   3.750   0.7123   0.02226   0.01369  -0.0719   0.6614   0.9460
   4.250   0.7568   0.02264   0.01417  -0.0710   0.6482   0.9597
   4.500   0.7999   0.02228   0.01383  -0.0738   0.6449   0.9630
   4.750   0.8159   0.02284   0.01447  -0.0729   0.6357   0.9772
   5.000   0.8546   0.02255   0.01424  -0.0750   0.6308   0.9906
   5.250   0.8725   0.02284   0.01457  -0.0740   0.6231   1.0000
   5.500   0.8992   0.02287   0.01465  -0.0743   0.6162   1.0000
   5.750   0.9296   0.02279   0.01462  -0.0750   0.6100   1.0000
   6.000   0.9480   0.02314   0.01503  -0.0741   0.6010   1.0000
   6.250   0.9748   0.02319   0.01513  -0.0744   0.5934   1.0000
   6.500   0.9985   0.02334   0.01536  -0.0742   0.5847   1.0000
   6.750   1.0171   0.02372   0.01581  -0.0733   0.5749   1.0000
   7.000   1.0519   0.02341   0.01553  -0.0744   0.5671   1.0000
   7.250   1.0642   0.02403   0.01625  -0.0728   0.5551   1.0000
   7.500   1.0846   0.02433   0.01661  -0.0721   0.5439   1.0000
   7.750   1.1118   0.02430   0.01662  -0.0722   0.5330   1.0000
   8.000   1.1337   0.02452   0.01690  -0.0716   0.5205   1.0000
   8.250   1.1493   0.02505   0.01749  -0.0704   0.5066   1.0000
   8.500   1.1667   0.02551   0.01800  -0.0693   0.4922   1.0000
   8.750   1.1841   0.02598   0.01852  -0.0683   0.4771   1.0000
   9.000   1.2009   0.02650   0.01907  -0.0671   0.4612   1.0000
   9.250   1.2168   0.02708   0.01966  -0.0659   0.4444   1.0000
   9.500   1.2319   0.02773   0.02029  -0.0647   0.4270   1.0000
   9.750   1.2433   0.02863   0.02122  -0.0631   0.4090   1.0000
  10.000   1.2534   0.02964   0.02223  -0.0615   0.3905   1.0000
  10.250   1.2628   0.03073   0.02332  -0.0599   0.3718   1.0000
  10.500   1.2714   0.03191   0.02448  -0.0583   0.3534   1.0000
  10.750   1.2788   0.03321   0.02576  -0.0567   0.3351   1.0000
  11.000   1.2851   0.03463   0.02715  -0.0551   0.3173   1.0000
  11.250   1.2904   0.03620   0.02873  -0.0536   0.2997   1.0000
  11.500   1.2948   0.03787   0.03040  -0.0521   0.2823   1.0000
  11.750   1.2987   0.03964   0.03217  -0.0507   0.2656   1.0000
  12.000   1.3022   0.04150   0.03404  -0.0494   0.2494   1.0000
  12.250   1.3050   0.04349   0.03605  -0.0481   0.2337   1.0000
  12.500   1.3076   0.04556   0.03814  -0.0470   0.2189   1.0000
  12.750   1.3095   0.04777   0.04037  -0.0460   0.2044   1.0000
  13.000   1.3113   0.05008   0.04270  -0.0451   0.1907   1.0000
  13.250   1.3124   0.05253   0.04517  -0.0443   0.1776   1.0000
  13.500   1.3129   0.05511   0.04777  -0.0436   0.1653   1.0000
  14.000   1.3132   0.06062   0.05338  -0.0427   0.1421   1.0000
  14.250   1.3134   0.06350   0.05633  -0.0424   0.1315   1.0000
  14.500   1.3125   0.06659   0.05946  -0.0422   0.1219   1.0000
  14.750   1.3099   0.06995   0.06284  -0.0422   0.1132   1.0000
  15.000   1.3097   0.07316   0.06616  -0.0423   0.1041   1.0000
  15.250   1.3077   0.07663   0.06970  -0.0426   0.0966   1.0000
  15.500   1.3045   0.08036   0.07349  -0.0430   0.0897   1.0000
  15.750   1.3028   0.08396   0.07721  -0.0435   0.0831   1.0000
  16.000   1.2984   0.08802   0.08132  -0.0443   0.0777   1.0000
  16.250   1.2967   0.09179   0.08522  -0.0451   0.0720   1.0000
  16.500   1.2922   0.09600   0.08950  -0.0461   0.0675   1.0000
  16.750   1.2895   0.10002   0.09363  -0.0472   0.0631   1.0000
  17.000   1.2859   0.10426   0.09799  -0.0485   0.0590   1.0000
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