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EPPLER 432 AIRFOIL (e432-il) Xfoil prediction polar at RE=231,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 432 AIRFOIL (e432-il)
Reynolds number: 231,000
Max Cl/Cd: 81.82 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e432-il-231000.txt
Download as CSV file: xf-e432-il-231000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 432 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.231 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1685   0.09961   0.09656  -0.0785   0.9627   0.0397
 -10.000  -0.1564   0.09438   0.09133  -0.0847   0.9517   0.0420
  -9.500  -0.1296   0.08124   0.07816  -0.1014   0.9326   0.0447
  -9.250  -0.1022   0.07731   0.07418  -0.1068   0.9215   0.0461
  -9.000  -0.0813   0.07135   0.06814  -0.1159   0.9066   0.0482
  -8.750  -0.0903   0.06154   0.05812  -0.1309   0.8819   0.0505
  -8.250  -0.1579   0.05622   0.05200  -0.1298   0.8379   0.0516
  -8.000  -0.1455   0.05098   0.04683  -0.1304   0.8289   0.0526
  -7.750  -0.1326   0.04873   0.04455  -0.1298   0.8192   0.0536
  -7.500  -0.1252   0.04668   0.04241  -0.1289   0.8098   0.0549
  -6.500  -0.1122   0.02893   0.02257  -0.1205   0.7810   0.0319
  -6.250  -0.0959   0.02526   0.01798  -0.1178   0.7744   0.0257
  -6.000  -0.0722   0.02326   0.01578  -0.1173   0.7691   0.0253
  -5.750  -0.0482   0.02171   0.01399  -0.1166   0.7638   0.0251
  -5.500  -0.0239   0.02045   0.01254  -0.1159   0.7579   0.0253
  -5.250   0.0017   0.01928   0.01118  -0.1153   0.7529   0.0259
  -5.000   0.0261   0.01832   0.01023  -0.1148   0.7482   0.0272
  -4.750   0.0494   0.01763   0.00952  -0.1140   0.7428   0.0289
  -4.500   0.0731   0.01693   0.00879  -0.1134   0.7380   0.0322
  -4.250   0.0984   0.01641   0.00821  -0.1131   0.7339   0.0374
  -4.000   0.1196   0.01575   0.00763  -0.1121   0.7287   0.0461
  -3.750   0.1427   0.01511   0.00709  -0.1116   0.7239   0.0683
  -3.500   0.1662   0.01432   0.00657  -0.1113   0.7199   0.1304
  -3.250   0.1873   0.01316   0.00621  -0.1113   0.7160   0.3190
  -3.000   0.2017   0.01216   0.00658  -0.1091   0.7110   0.6465
  -2.750   0.2261   0.01254   0.00696  -0.1077   0.7066   0.7133
  -2.500   0.2522   0.01296   0.00726  -0.1066   0.7029   0.7432
  -2.250   0.2764   0.01341   0.00763  -0.1051   0.6993   0.7629
  -2.000   0.2977   0.01380   0.00800  -0.1031   0.6945   0.7792
  -1.750   0.3204   0.01413   0.00827  -0.1014   0.6902   0.7933
  -1.500   0.3424   0.01444   0.00850  -0.0993   0.6867   0.8034
  -1.250   0.3665   0.01471   0.00867  -0.0980   0.6834   0.8145
  -1.000   0.3866   0.01494   0.00890  -0.0961   0.6787   0.8272
  -0.750   0.4029   0.01521   0.00916  -0.0927   0.6745   0.8401
  -0.500   0.4212   0.01540   0.00930  -0.0898   0.6710   0.8524
  -0.250   0.4463   0.01550   0.00929  -0.0890   0.6680   0.8617
   0.000   0.4663   0.01554   0.00934  -0.0874   0.6635   0.8674
   0.250   0.4918   0.01556   0.00931  -0.0873   0.6591   0.8729
   0.500   0.5182   0.01552   0.00920  -0.0872   0.6554   0.8765
   0.750   0.5462   0.01552   0.00910  -0.0873   0.6523   0.8795
   1.000   0.5700   0.01556   0.00914  -0.0869   0.6481   0.8832
   1.250   0.5953   0.01560   0.00917  -0.0868   0.6436   0.8870
   1.500   0.6240   0.01561   0.00913  -0.0875   0.6398   0.8902
   1.750   0.6522   0.01559   0.00903  -0.0877   0.6365   0.8925
   2.000   0.6769   0.01565   0.00909  -0.0873   0.6327   0.8956
   2.250   0.7003   0.01571   0.00918  -0.0869   0.6280   0.8988
   2.500   0.7283   0.01574   0.00918  -0.0873   0.6239   0.9017
   2.750   0.7600   0.01578   0.00915  -0.0885   0.6205   0.9047
   3.000   0.7847   0.01583   0.00921  -0.0881   0.6167   0.9074
   3.250   0.8063   0.01589   0.00934  -0.0873   0.6117   0.9105
   3.500   0.8333   0.01591   0.00934  -0.0875   0.6074   0.9135
   3.750   0.8644   0.01592   0.00929  -0.0884   0.6039   0.9164
   4.000   0.8895   0.01605   0.00947  -0.0883   0.5993   0.9200
   4.250   0.9105   0.01606   0.00955  -0.0873   0.5941   0.9235
   4.500   0.9381   0.01604   0.00951  -0.0875   0.5899   0.9267
   4.750   0.9706   0.01607   0.00947  -0.0886   0.5863   0.9296
   5.000   0.9896   0.01620   0.00973  -0.0875   0.5802   0.9340
   5.250   1.0130   0.01615   0.00972  -0.0868   0.5753   0.9382
   5.500   1.0433   0.01610   0.00962  -0.0875   0.5713   0.9422
   5.750   1.0639   0.01622   0.00985  -0.0865   0.5655   0.9474
   6.000   1.0871   0.01619   0.00987  -0.0859   0.5599   0.9522
   6.250   1.1183   0.01613   0.00977  -0.0868   0.5555   0.9566
   6.500   1.1391   0.01623   0.01000  -0.0859   0.5491   0.9630
   6.750   1.1667   0.01620   0.01002  -0.0862   0.5431   0.9696
   7.000   1.2011   0.01620   0.01001  -0.0879   0.5379   0.9753
   7.250   1.2283   0.01632   0.01028  -0.0885   0.5301   0.9849
   7.750   1.2843   0.01648   0.01054  -0.0898   0.5161   1.0000
   8.000   1.3133   0.01650   0.01057  -0.0905   0.5091   1.0000
   8.250   1.3350   0.01670   0.01088  -0.0901   0.5005   1.0000
   8.500   1.3637   0.01677   0.01092  -0.0908   0.4927   1.0000
   8.750   1.3823   0.01701   0.01130  -0.0899   0.4829   1.0000
   9.000   1.4059   0.01719   0.01149  -0.0897   0.4738   1.0000
   9.250   1.4244   0.01741   0.01177  -0.0886   0.4634   1.0000
   9.500   1.4383   0.01773   0.01217  -0.0867   0.4524   1.0000
   9.750   1.4535   0.01807   0.01253  -0.0851   0.4413   1.0000
  10.000   1.4672   0.01848   0.01293  -0.0833   0.4294   1.0000
  10.250   1.4766   0.01902   0.01351  -0.0809   0.4163   1.0000
  10.500   1.4839   0.01969   0.01421  -0.0783   0.4023   1.0000
  10.750   1.4896   0.02049   0.01503  -0.0757   0.3878   1.0000
  11.000   1.4934   0.02145   0.01599  -0.0729   0.3726   1.0000
  11.250   1.4956   0.02260   0.01712  -0.0702   0.3570   1.0000
  11.500   1.4961   0.02395   0.01845  -0.0676   0.3409   1.0000
  11.750   1.4950   0.02553   0.02000  -0.0650   0.3247   1.0000
  12.000   1.4928   0.02730   0.02174  -0.0626   0.3086   1.0000
  12.250   1.4899   0.02927   0.02368  -0.0604   0.2927   1.0000
  12.500   1.4867   0.03139   0.02577  -0.0585   0.2773   1.0000
  12.750   1.4832   0.03366   0.02801  -0.0567   0.2626   1.0000
  13.000   1.4793   0.03608   0.03041  -0.0551   0.2481   1.0000
  13.250   1.4759   0.03858   0.03291  -0.0538   0.2341   1.0000
  13.500   1.4724   0.04120   0.03553  -0.0526   0.2203   1.0000
  13.750   1.4692   0.04391   0.03825  -0.0516   0.2071   1.0000
  14.000   1.4657   0.04673   0.04107  -0.0508   0.1943   1.0000
  14.250   1.4625   0.04964   0.04398  -0.0501   0.1825   1.0000
  14.500   1.4585   0.05272   0.04706  -0.0496   0.1710   1.0000
  14.750   1.4535   0.05599   0.05030  -0.0492   0.1601   1.0000
  15.000   1.4506   0.05916   0.05350  -0.0490   0.1491   1.0000
  15.250   1.4482   0.06237   0.05674  -0.0489   0.1387   1.0000
  15.500   1.4445   0.06581   0.06019  -0.0489   0.1292   1.0000
  15.750   1.4385   0.06958   0.06394  -0.0490   0.1206   1.0000
  16.000   1.4367   0.07297   0.06739  -0.0493   0.1114   1.0000
  16.250   1.4331   0.07664   0.07109  -0.0497   0.1034   1.0000
  16.500   1.4272   0.08067   0.07510  -0.0502   0.0962   1.0000
  16.750   1.4252   0.08429   0.07881  -0.0508   0.0887   1.0000
  17.000   1.4190   0.08849   0.08299  -0.0516   0.0827   1.0000
  17.250   1.4170   0.09225   0.08684  -0.0524   0.0764   1.0000
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