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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 200,000
Max Cl/Cd: 79.78 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e431-il-200000.txt
Download as CSV file: xf-e431-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1371   0.09263   0.08919  -0.0991   0.9575   0.0442
  -9.500  -0.1300   0.08769   0.08426  -0.1049   0.9508   0.0460
  -9.250  -0.1389   0.07588   0.07239  -0.1268   0.9451   0.0473
  -9.000  -0.1205   0.07315   0.06974  -0.1240   0.9403   0.0483
  -8.750  -0.0990   0.07113   0.06770  -0.1242   0.9362   0.0496
  -8.500  -0.0854   0.06558   0.06212  -0.1320   0.9315   0.0514
  -8.250  -0.0906   0.06055   0.05700  -0.1375   0.9203   0.0524
  -8.000  -0.1026   0.05674   0.05303  -0.1399   0.9094   0.0539
  -7.750  -0.1389   0.05521   0.05079  -0.1389   0.8952   0.0564
  -7.500  -0.1261   0.04978   0.04553  -0.1394   0.8897   0.0577
  -7.250  -0.1074   0.04720   0.04294  -0.1400   0.8854   0.0592
  -7.000  -0.1001   0.04524   0.04087  -0.1387   0.8788   0.0615
  -6.750  -0.1061   0.04340   0.03841  -0.1363   0.8707   0.0679
  -6.500  -0.0832   0.04004   0.03511  -0.1372   0.8676   0.0698
  -6.250  -0.0903   0.03002   0.02375  -0.1303   0.8590   0.0290
  -6.000  -0.0689   0.02725   0.02053  -0.1292   0.8550   0.0260
  -5.750  -0.0427   0.02447   0.01718  -0.1287   0.8520   0.0242
  -5.500  -0.0251   0.02316   0.01557  -0.1267   0.8463   0.0240
  -5.250  -0.0016   0.02202   0.01434  -0.1259   0.8416   0.0247
  -5.000   0.0261   0.02091   0.01309  -0.1258   0.8383   0.0259
  -4.750   0.0552   0.02000   0.01209  -0.1261   0.8356   0.0294
  -4.500   0.0717   0.01967   0.01175  -0.1242   0.8298   0.0320
  -4.250   0.0935   0.01883   0.01093  -0.1232   0.8252   0.0354
  -4.000   0.1190   0.01800   0.01009  -0.1229   0.8219   0.0414
  -3.750   0.1463   0.01716   0.00933  -0.1230   0.8192   0.0619
  -3.500   0.1587   0.01650   0.00902  -0.1208   0.8128   0.1205
  -3.250   0.1765   0.01490   0.00860  -0.1206   0.8084   0.3767
  -3.000   0.1935   0.01441   0.00925  -0.1177   0.8052   0.6889
  -2.750   0.2206   0.01491   0.00965  -0.1164   0.8027   0.7386
  -2.500   0.2335   0.01554   0.01024  -0.1131   0.7962   0.7625
  -2.250   0.2530   0.01600   0.01065  -0.1104   0.7921   0.7811
  -2.000   0.2762   0.01634   0.01090  -0.1083   0.7891   0.7979
  -1.750   0.3011   0.01662   0.01107  -0.1066   0.7867   0.8132
  -1.500   0.3083   0.01710   0.01156  -0.1023   0.7798   0.8251
  -1.250   0.3265   0.01727   0.01168  -0.0996   0.7757   0.8358
  -1.000   0.3475   0.01739   0.01172  -0.0971   0.7728   0.8502
  -0.750   0.3635   0.01759   0.01187  -0.0935   0.7695   0.8669
  -0.500   0.3665   0.01787   0.01218  -0.0883   0.7626   0.8804
  -0.250   0.3911   0.01782   0.01204  -0.0876   0.7589   0.8899
   0.000   0.4221   0.01763   0.01175  -0.0880   0.7563   0.8938
   0.250   0.4420   0.01769   0.01178  -0.0868   0.7517   0.8990
   0.500   0.4596   0.01780   0.01186  -0.0855   0.7457   0.9044
   0.750   0.4888   0.01761   0.01160  -0.0858   0.7423   0.9074
   1.000   0.5241   0.01741   0.01131  -0.0873   0.7397   0.9099
   1.250   0.5379   0.01760   0.01151  -0.0852   0.7335   0.9147
   1.500   0.5630   0.01759   0.01148  -0.0852   0.7285   0.9182
   1.750   0.5964   0.01738   0.01120  -0.0863   0.7253   0.9207
   2.000   0.6337   0.01717   0.01092  -0.0882   0.7228   0.9228
   2.250   0.6414   0.01742   0.01124  -0.0850   0.7148   0.9277
   2.500   0.6723   0.01729   0.01108  -0.0858   0.7107   0.9309
   2.750   0.7100   0.01707   0.01079  -0.0878   0.7077   0.9334
   3.000   0.7248   0.01719   0.01097  -0.0858   0.7010   0.9375
   3.250   0.7523   0.01709   0.01087  -0.0859   0.6958   0.9408
   3.500   0.7898   0.01683   0.01058  -0.0879   0.6923   0.9433
   3.750   0.8088   0.01691   0.01070  -0.0866   0.6858   0.9482
   4.000   0.8364   0.01679   0.01059  -0.0868   0.6799   0.9521
   4.250   0.8753   0.01650   0.01026  -0.0889   0.6761   0.9547
   4.500   0.8928   0.01661   0.01046  -0.0875   0.6686   0.9603
   4.750   0.9274   0.01640   0.01026  -0.0889   0.6629   0.9634
   5.000   0.9660   0.01618   0.01003  -0.0911   0.6581   0.9666
   5.250   0.9879   0.01624   0.01019  -0.0905   0.6495   0.9732
   5.500   1.0310   0.01595   0.00986  -0.0935   0.6442   0.9757
   5.750   1.0561   0.01603   0.01007  -0.0936   0.6349   0.9824
   6.000   1.0987   0.01575   0.00976  -0.0966   0.6284   0.9851
   6.250   1.1261   0.01580   0.00993  -0.0972   0.6178   0.9942
   6.500   1.1531   0.01570   0.00985  -0.0974   0.6095   1.0000
   6.750   1.1738   0.01566   0.00985  -0.0965   0.5997   1.0000
   7.000   1.1940   0.01573   0.00999  -0.0956   0.5889   1.0000
   7.250   1.2203   0.01573   0.01001  -0.0957   0.5782   1.0000
   7.500   1.2470   0.01575   0.01002  -0.0959   0.5664   1.0000
   7.750   1.2660   0.01592   0.01026  -0.0948   0.5524   1.0000
   8.000   1.2844   0.01610   0.01048  -0.0935   0.5378   1.0000
   8.250   1.3022   0.01634   0.01073  -0.0922   0.5222   1.0000
   8.500   1.3191   0.01666   0.01104  -0.0907   0.5055   1.0000
   8.750   1.3334   0.01708   0.01145  -0.0889   0.4875   1.0000
   9.000   1.3446   0.01761   0.01198  -0.0867   0.4685   1.0000
   9.250   1.3544   0.01825   0.01258  -0.0843   0.4484   1.0000
   9.500   1.3632   0.01899   0.01326  -0.0818   0.4283   1.0000
   9.750   1.3693   0.01988   0.01409  -0.0791   0.4075   1.0000
  10.000   1.3744   0.02088   0.01506  -0.0764   0.3868   1.0000
  10.250   1.3784   0.02201   0.01612  -0.0737   0.3665   1.0000
  10.500   1.3815   0.02326   0.01731  -0.0710   0.3466   1.0000
  10.750   1.3840   0.02463   0.01864  -0.0685   0.3264   1.0000
  11.000   1.3858   0.02612   0.02008  -0.0661   0.3071   1.0000
  11.250   1.3868   0.02773   0.02163  -0.0637   0.2886   1.0000
  11.500   1.3879   0.02943   0.02329  -0.0616   0.2705   1.0000
  11.750   1.3895   0.03119   0.02503  -0.0596   0.2525   1.0000
  12.000   1.3906   0.03306   0.02688  -0.0578   0.2351   1.0000
  12.250   1.3914   0.03504   0.02883  -0.0561   0.2186   1.0000
  12.500   1.3917   0.03713   0.03089  -0.0545   0.2025   1.0000
  12.750   1.3920   0.03932   0.03306  -0.0531   0.1871   1.0000
  13.000   1.3924   0.04159   0.03532  -0.0518   0.1725   1.0000
  13.250   1.3926   0.04396   0.03767  -0.0506   0.1587   1.0000
  13.500   1.3925   0.04645   0.04016  -0.0496   0.1455   1.0000
  13.750   1.3923   0.04904   0.04275  -0.0487   0.1333   1.0000
  14.000   1.3913   0.05180   0.04550  -0.0479   0.1220   1.0000
  14.250   1.3889   0.05477   0.04844  -0.0472   0.1119   1.0000
  14.500   1.3880   0.05771   0.05140  -0.0467   0.1019   1.0000
  14.750   1.3878   0.06064   0.05439  -0.0463   0.0926   1.0000
  15.000   1.3854   0.06391   0.05767  -0.0460   0.0847   1.0000
  15.250   1.3820   0.06735   0.06111  -0.0459   0.0778   1.0000
  15.500   1.3820   0.07053   0.06439  -0.0459   0.0710   1.0000
  15.750   1.3773   0.07425   0.06806  -0.0459   0.0657   1.0000
  16.000   1.3779   0.07753   0.07149  -0.0462   0.0602   1.0000
  16.250   1.3736   0.08132   0.07523  -0.0465   0.0559   1.0000
  16.500   1.3740   0.08476   0.07885  -0.0470   0.0517   1.0000
  16.750   1.3710   0.08856   0.08264  -0.0477   0.0482   1.0000
  17.000   1.3705   0.09214   0.08636  -0.0482   0.0448   1.0000
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