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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 200,000
Max Cl/Cd: 76.79 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e431-il-200000-n5.txt
Download as CSV file: xf-e431-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2274   0.13003   0.12634  -0.0710   0.9813   0.0230
 -12.250  -0.2203   0.12538   0.12170  -0.0747   0.9744   0.0231
 -12.000  -0.2128   0.12089   0.11722  -0.0780   0.9670   0.0232
 -11.750  -0.2037   0.11635   0.11268  -0.0815   0.9607   0.0232
 -11.500  -0.1946   0.11183   0.10817  -0.0849   0.9538   0.0232
 -11.250  -0.1836   0.10719   0.10352  -0.0887   0.9479   0.0232
 -11.000  -0.1716   0.10254   0.09885  -0.0928   0.9423   0.0232
 -10.500  -0.1492   0.09094   0.08718  -0.0997   0.9317   0.0125
 -10.250  -0.1366   0.08642   0.08264  -0.1043   0.9246   0.0122
 -10.000  -0.1237   0.08143   0.07763  -0.1099   0.9176   0.0119
  -9.750  -0.1160   0.07539   0.07156  -0.1160   0.9088   0.0116
  -9.500  -0.1436   0.05696   0.05302  -0.1321   0.8949   0.0099
  -9.250  -0.1512   0.05084   0.04670  -0.1380   0.8817   0.0098
  -9.000  -0.1663   0.04629   0.04193  -0.1397   0.8681   0.0097
  -8.750  -0.1820   0.04339   0.03883  -0.1381   0.8558   0.0097
  -8.500  -0.1944   0.04022   0.03539  -0.1360   0.8466   0.0096
  -8.250  -0.1988   0.03728   0.03215  -0.1341   0.8386   0.0095
  -8.000  -0.1999   0.03416   0.02866  -0.1321   0.8318   0.0094
  -7.750  -0.1961   0.03135   0.02545  -0.1301   0.8251   0.0093
  -7.500  -0.1865   0.02853   0.02215  -0.1285   0.8201   0.0093
  -7.250  -0.1730   0.02635   0.01958  -0.1270   0.8150   0.0094
  -7.000  -0.1565   0.02430   0.01711  -0.1256   0.8098   0.0095
  -6.750  -0.1355   0.02276   0.01524  -0.1248   0.8056   0.0096
  -6.500  -0.1127   0.02141   0.01358  -0.1241   0.8018   0.0099
  -6.250  -0.0921   0.02040   0.01247  -0.1232   0.7972   0.0103
  -6.000  -0.0696   0.01960   0.01157  -0.1226   0.7929   0.0107
  -5.750  -0.0458   0.01884   0.01068  -0.1222   0.7892   0.0112
  -5.500  -0.0218   0.01812   0.00982  -0.1217   0.7858   0.0119
  -5.250   0.0002   0.01759   0.00924  -0.1210   0.7813   0.0133
  -5.000   0.0239   0.01714   0.00873  -0.1205   0.7774   0.0152
  -4.750   0.0480   0.01662   0.00815  -0.1201   0.7738   0.0172
  -4.500   0.0737   0.01612   0.00751  -0.1199   0.7708   0.0192
  -4.250   0.0963   0.01568   0.00707  -0.1192   0.7666   0.0229
  -4.000   0.1200   0.01526   0.00668  -0.1188   0.7626   0.0310
  -3.750   0.1448   0.01480   0.00627  -0.1185   0.7590   0.0487
  -3.500   0.1704   0.01433   0.00593  -0.1185   0.7559   0.0857
  -3.250   0.1947   0.01383   0.00569  -0.1184   0.7524   0.1498
  -3.000   0.2171   0.01318   0.00548  -0.1182   0.7483   0.2610
  -2.750   0.2394   0.01224   0.00525  -0.1182   0.7445   0.4521
  -2.500   0.2600   0.01193   0.00563  -0.1164   0.7413   0.6471
  -2.250   0.2876   0.01209   0.00573  -0.1160   0.7386   0.6966
  -2.000   0.3112   0.01229   0.00593  -0.1149   0.7344   0.7211
  -1.750   0.3364   0.01247   0.00604  -0.1142   0.7304   0.7391
  -1.500   0.3625   0.01263   0.00612  -0.1136   0.7269   0.7530
  -1.250   0.3878   0.01286   0.00628  -0.1127   0.7238   0.7700
  -1.000   0.4097   0.01315   0.00655  -0.1109   0.7203   0.7869
  -0.750   0.4325   0.01331   0.00668  -0.1097   0.7160   0.7978
  -0.500   0.4580   0.01337   0.00668  -0.1092   0.7122   0.8023
  -0.250   0.4865   0.01338   0.00660  -0.1095   0.7088   0.8063
   0.000   0.5165   0.01339   0.00651  -0.1102   0.7057   0.8100
   0.250   0.5408   0.01343   0.00655  -0.1098   0.7009   0.8127
   0.500   0.5668   0.01345   0.00654  -0.1095   0.6967   0.8149
   0.750   0.5947   0.01346   0.00649  -0.1097   0.6931   0.8175
   1.000   0.6232   0.01349   0.00645  -0.1100   0.6895   0.8201
   1.250   0.6480   0.01354   0.00652  -0.1097   0.6843   0.8229
   1.500   0.6759   0.01357   0.00651  -0.1100   0.6798   0.8260
   1.750   0.7046   0.01357   0.00647  -0.1104   0.6759   0.8283
   2.000   0.7290   0.01363   0.00655  -0.1099   0.6710   0.8305
   2.250   0.7538   0.01367   0.00661  -0.1095   0.6656   0.8328
   2.500   0.7815   0.01368   0.00659  -0.1097   0.6611   0.8351
   2.750   0.8077   0.01374   0.00665  -0.1096   0.6560   0.8380
   3.000   0.8328   0.01380   0.00675  -0.1094   0.6500   0.8413
   3.250   0.8609   0.01382   0.00674  -0.1096   0.6449   0.8437
   3.500   0.8839   0.01388   0.00685  -0.1089   0.6387   0.8460
   3.750   0.9080   0.01393   0.00692  -0.1083   0.6323   0.8485
   4.000   0.9345   0.01396   0.00697  -0.1082   0.6264   0.8511
   4.250   0.9570   0.01406   0.00712  -0.1075   0.6188   0.8545
   4.500   0.9849   0.01409   0.00713  -0.1077   0.6126   0.8577
   4.750   1.0052   0.01420   0.00733  -0.1065   0.6041   0.8607
   5.250   1.0499   0.01436   0.00757  -0.1048   0.5879   0.8667
   5.500   1.0732   0.01445   0.00768  -0.1041   0.5793   0.8701
   5.750   1.0949   0.01458   0.00784  -0.1032   0.5692   0.8739
   6.000   1.1133   0.01470   0.00802  -0.1016   0.5588   0.8775
   6.250   1.1322   0.01483   0.00817  -0.1000   0.5477   0.8818
   6.500   1.1504   0.01500   0.00835  -0.0984   0.5359   0.8865
   6.750   1.1656   0.01518   0.00858  -0.0963   0.5230   0.8911
   7.000   1.1799   0.01541   0.00883  -0.0940   0.5096   0.8962
   7.250   1.1949   0.01570   0.00914  -0.0919   0.4953   0.9021
   7.500   1.2074   0.01601   0.00946  -0.0894   0.4801   0.9087
   7.750   1.2190   0.01639   0.00984  -0.0868   0.4638   0.9171
   8.000   1.2288   0.01680   0.01026  -0.0839   0.4471   0.9272
   8.250   1.2379   0.01729   0.01075  -0.0811   0.4294   0.9415
   8.750   1.2602   0.01861   0.01201  -0.0772   0.3912   1.0000
   9.000   1.2706   0.01949   0.01285  -0.0753   0.3721   1.0000
   9.250   1.2789   0.02050   0.01381  -0.0733   0.3525   1.0000
   9.500   1.2864   0.02160   0.01485  -0.0712   0.3341   1.0000
   9.750   1.2935   0.02276   0.01597  -0.0693   0.3152   1.0000
  10.000   1.3005   0.02399   0.01716  -0.0674   0.2973   1.0000
  10.250   1.3066   0.02532   0.01845  -0.0655   0.2794   1.0000
  10.500   1.3124   0.02672   0.01983  -0.0638   0.2623   1.0000
  10.750   1.3179   0.02819   0.02127  -0.0621   0.2459   1.0000
  11.000   1.3231   0.02974   0.02279  -0.0604   0.2298   1.0000
  11.250   1.3280   0.03135   0.02438  -0.0589   0.2144   1.0000
  11.500   1.3328   0.03304   0.02604  -0.0575   0.1993   1.0000
  11.750   1.3377   0.03477   0.02778  -0.0561   0.1850   1.0000
  12.000   1.3423   0.03658   0.02958  -0.0549   0.1711   1.0000
  12.250   1.3468   0.03845   0.03144  -0.0537   0.1581   1.0000
  12.500   1.3512   0.04039   0.03338  -0.0527   0.1456   1.0000
  12.750   1.3553   0.04242   0.03542  -0.0517   0.1338   1.0000
  13.000   1.3587   0.04457   0.03756  -0.0508   0.1226   1.0000
  13.250   1.3616   0.04681   0.03982  -0.0500   0.1123   1.0000
  13.500   1.3655   0.04904   0.04207  -0.0493   0.1022   1.0000
  13.750   1.3693   0.05133   0.04441  -0.0487   0.0932   1.0000
  14.000   1.3719   0.05380   0.04691  -0.0482   0.0853   1.0000
  14.250   1.3739   0.05639   0.04953  -0.0477   0.0778   1.0000
  14.500   1.3770   0.05894   0.05214  -0.0474   0.0708   1.0000
  14.750   1.3778   0.06181   0.05505  -0.0472   0.0650   1.0000
  15.000   1.3799   0.06459   0.05791  -0.0471   0.0591   1.0000
  15.250   1.3804   0.06762   0.06101  -0.0471   0.0543   1.0000
  15.500   1.3809   0.07074   0.06420  -0.0472   0.0496   1.0000
  15.750   1.3804   0.07406   0.06760  -0.0475   0.0459   1.0000
  16.000   1.3803   0.07739   0.07101  -0.0478   0.0420   1.0000
  16.250   1.3780   0.08106   0.07476  -0.0483   0.0390   1.0000
  16.500   1.3777   0.08456   0.07839  -0.0489   0.0360   1.0000
  16.750   1.3739   0.08863   0.08252  -0.0498   0.0336   1.0000
  17.000   1.3725   0.09243   0.08646  -0.0507   0.0312   1.0000
  17.250   1.3698   0.09646   0.09060  -0.0517   0.0292   1.0000
  17.500   1.3640   0.10105   0.09527  -0.0531   0.0276   1.0000
  17.750   1.3622   0.10506   0.09943  -0.0544   0.0257   1.0000
  18.000   1.3586   0.10944   0.10393  -0.0559   0.0241   1.0000
  18.250   1.3524   0.11430   0.10887  -0.0578   0.0230   1.0000
  18.500   1.3486   0.11880   0.11351  -0.0596   0.0217   1.0000
  18.750   1.3448   0.12335   0.11820  -0.0616   0.0205   1.0000
  19.000   1.3396   0.12821   0.12317  -0.0639   0.0194   1.0000
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