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E231 (e231-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E231 (e231-il)
Reynolds number: 200,000
Max Cl/Cd: 68.53 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e231-il-200000-n5.txt
Download as CSV file: xf-e231-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E231                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3650   0.11217   0.10864  -0.0484   1.0000   0.0216
 -11.000  -0.3651   0.10814   0.10466  -0.0501   1.0000   0.0217
 -10.750  -0.3639   0.10398   0.10051  -0.0487   1.0000   0.0146
 -10.500  -0.3666   0.09616   0.09271  -0.0532   0.9902   0.0107
 -10.250  -0.3605   0.09148   0.08805  -0.0571   0.9797   0.0105
 -10.000  -0.3533   0.08678   0.08334  -0.0614   0.9712   0.0102
  -9.750  -0.3479   0.08137   0.07794  -0.0666   0.9627   0.0099
  -9.500  -0.3461   0.07468   0.07125  -0.0733   0.9541   0.0095
  -9.250  -0.3489   0.06663   0.06317  -0.0827   0.9436   0.0094
  -9.000  -0.3618   0.06013   0.05653  -0.0875   0.9317   0.0092
  -8.750  -0.3762   0.05565   0.05189  -0.0878   0.9208   0.0089
  -8.500  -0.3914   0.05186   0.04792  -0.0856   0.9119   0.0087
  -8.250  -0.4057   0.04707   0.04284  -0.0828   0.9038   0.0083
  -8.000  -0.4208   0.04018   0.03531  -0.0784   0.8967   0.0075
  -7.750  -0.4201   0.03725   0.03207  -0.0756   0.8910   0.0074
  -7.500  -0.4159   0.03441   0.02885  -0.0729   0.8868   0.0074
  -7.250  -0.4081   0.03178   0.02585  -0.0705   0.8818   0.0073
  -7.000  -0.3967   0.02936   0.02304  -0.0682   0.8774   0.0073
  -6.750  -0.3819   0.02713   0.02040  -0.0662   0.8740   0.0073
  -6.500  -0.3642   0.02507   0.01792  -0.0645   0.8707   0.0074
  -6.250  -0.3441   0.02352   0.01610  -0.0633   0.8667   0.0074
  -6.000  -0.3229   0.02179   0.01408  -0.0622   0.8634   0.0077
  -5.750  -0.3006   0.02057   0.01270  -0.0613   0.8605   0.0080
  -5.250  -0.2554   0.01876   0.01066  -0.0596   0.8541   0.0088
  -5.000  -0.2330   0.01801   0.00981  -0.0586   0.8506   0.0098
  -4.750  -0.2098   0.01746   0.00913  -0.0578   0.8476   0.0109
  -4.500  -0.1872   0.01686   0.00850  -0.0570   0.8449   0.0133
  -4.250  -0.1649   0.01631   0.00784  -0.0560   0.8417   0.0154
  -4.000  -0.1437   0.01569   0.00717  -0.0548   0.8377   0.0184
  -3.750  -0.1212   0.01516   0.00662  -0.0538   0.8344   0.0268
  -3.500  -0.0994   0.01453   0.00614  -0.0527   0.8315   0.0604
  -3.250  -0.0797   0.01380   0.00579  -0.0516   0.8287   0.1482
  -3.000  -0.0633   0.01307   0.00559  -0.0499   0.8240   0.2740
  -2.750  -0.0505   0.01217   0.00539  -0.0474   0.8202   0.4449
  -2.500  -0.0382   0.01128   0.00527  -0.0442   0.8170   0.6316
  -2.250  -0.0027   0.01122   0.00575  -0.0443   0.8155   0.7927
  -2.000   0.0222   0.01150   0.00599  -0.0432   0.8111   0.8392
  -1.750   0.0478   0.01173   0.00613  -0.0422   0.8074   0.8646
  -1.500   0.0735   0.01190   0.00621  -0.0413   0.8043   0.8827
  -1.250   0.1052   0.01207   0.00626  -0.0415   0.8019   0.8958
  -1.000   0.1374   0.01228   0.00640  -0.0421   0.7980   0.9058
  -0.750   0.1661   0.01242   0.00647  -0.0421   0.7937   0.9159
  -0.500   0.2062   0.01251   0.00647  -0.0444   0.7905   0.9218
  -0.250   0.2369   0.01253   0.00639  -0.0448   0.7874   0.9295
   0.000   0.2775   0.01259   0.00642  -0.0475   0.7824   0.9330
   0.250   0.3114   0.01258   0.00636  -0.0488   0.7775   0.9376
   0.500   0.3386   0.01252   0.00623  -0.0486   0.7734   0.9431
   0.750   0.3743   0.01251   0.00621  -0.0505   0.7672   0.9456
   1.000   0.4083   0.01243   0.00610  -0.0518   0.7617   0.9484
   1.250   0.4379   0.01238   0.00602  -0.0523   0.7557   0.9521
   1.500   0.4613   0.01235   0.00598  -0.0515   0.7486   0.9568
   1.750   0.4955   0.01225   0.00587  -0.0529   0.7421   0.9586
   2.000   0.5273   0.01218   0.00582  -0.0539   0.7341   0.9609
   2.250   0.5574   0.01212   0.00576  -0.0545   0.7258   0.9636
   2.500   0.5856   0.01203   0.00566  -0.0547   0.7174   0.9665
   2.750   0.6088   0.01203   0.00569  -0.0539   0.7069   0.9702
   3.000   0.6404   0.01195   0.00565  -0.0549   0.6958   0.9719
   3.250   0.6708   0.01189   0.00559  -0.0556   0.6831   0.9738
   3.500   0.6997   0.01184   0.00555  -0.0559   0.6683   0.9760
   3.750   0.7272   0.01182   0.00554  -0.0560   0.6517   0.9785
   4.000   0.7528   0.01183   0.00552  -0.0557   0.6329   0.9810
   4.250   0.7780   0.01189   0.00555  -0.0553   0.6096   0.9835
   4.500   0.8062   0.01199   0.00556  -0.0556   0.5799   0.9853
   4.750   0.8318   0.01218   0.00564  -0.0554   0.5462   0.9874
   5.000   0.8553   0.01248   0.00580  -0.0549   0.5084   0.9900
   5.250   0.8769   0.01289   0.00605  -0.0541   0.4679   0.9930
   5.500   0.8981   0.01337   0.00636  -0.0534   0.4279   0.9955
   5.750   0.9195   0.01389   0.00674  -0.0529   0.3904   0.9983
   6.000   0.9366   0.01440   0.00714  -0.0514   0.3573   1.0000
   6.250   0.9440   0.01487   0.00752  -0.0479   0.3306   1.0000
   6.500   0.9499   0.01534   0.00790  -0.0441   0.3064   1.0000
   6.750   0.9546   0.01578   0.00828  -0.0401   0.2834   1.0000
   7.000   0.9569   0.01622   0.00865  -0.0356   0.2638   1.0000
   7.250   0.9574   0.01662   0.00902  -0.0308   0.2452   1.0000
   7.500   0.9543   0.01695   0.00933  -0.0253   0.2305   1.0000
   7.750   0.9541   0.01735   0.00968  -0.0205   0.2154   1.0000
   8.000   0.9578   0.01782   0.01012  -0.0165   0.1997   1.0000
   8.250   0.9639   0.01839   0.01064  -0.0133   0.1827   1.0000
   8.500   0.9721   0.01903   0.01123  -0.0105   0.1662   1.0000
   8.750   0.9820   0.01970   0.01187  -0.0081   0.1517   1.0000
   9.000   0.9928   0.02040   0.01255  -0.0060   0.1365   1.0000
   9.250   1.0041   0.02114   0.01330  -0.0040   0.1233   1.0000
   9.500   1.0151   0.02194   0.01410  -0.0021   0.1107   1.0000
  10.000   1.0379   0.02362   0.01580   0.0014   0.0878   1.0000
  10.250   1.0494   0.02451   0.01671   0.0030   0.0782   1.0000
  10.500   1.0600   0.02548   0.01771   0.0047   0.0699   1.0000
  10.750   1.0696   0.02656   0.01880   0.0063   0.0619   1.0000
  11.000   1.0806   0.02756   0.01987   0.0077   0.0542   1.0000
  11.250   1.0897   0.02872   0.02108   0.0093   0.0474   1.0000
  11.500   1.0987   0.02992   0.02231   0.0107   0.0407   1.0000
  11.750   1.1075   0.03117   0.02365   0.0121   0.0360   1.0000
  12.000   1.1146   0.03258   0.02510   0.0135   0.0308   1.0000
  12.250   1.1217   0.03403   0.02665   0.0149   0.0269   1.0000
  12.500   1.1272   0.03565   0.02831   0.0162   0.0229   1.0000
  12.750   1.1316   0.03740   0.03016   0.0175   0.0194   1.0000
  13.000   1.1352   0.03928   0.03213   0.0186   0.0165   1.0000
  13.250   1.1357   0.04147   0.03440   0.0197   0.0149   1.0000
  13.500   1.1398   0.04342   0.03649   0.0206   0.0125   1.0000
  13.750   1.1397   0.04584   0.03900   0.0214   0.0112   1.0000
  14.000   1.1362   0.04872   0.04203   0.0220   0.0101   1.0000
  14.250   1.1398   0.05097   0.04441   0.0223   0.0081   1.0000
  14.500   1.1352   0.05421   0.04783   0.0225   0.0081   1.0000
  14.750   1.1306   0.05762   0.05132   0.0222   0.0072   1.0000
  15.000   1.1268   0.06110   0.05497   0.0219   0.0067   1.0000
  15.250   1.1204   0.06508   0.05913   0.0211   0.0065   1.0000
  15.500   1.1125   0.06948   0.06371   0.0200   0.0063   1.0000
  15.750   1.1043   0.07415   0.06854   0.0185   0.0057   1.0000
  16.000   1.0947   0.07923   0.07379   0.0167   0.0057   1.0000
  16.250   1.0852   0.08450   0.07923   0.0146   0.0057   1.0000
  16.500   1.0739   0.09033   0.08522   0.0119   0.0054   1.0000
  16.750   1.0609   0.09666   0.09170   0.0090   0.0053   1.0000
  17.000   1.0487   0.10309   0.09829   0.0058   0.0052   1.0000
  17.250   1.0367   0.10962   0.10498   0.0025   0.0052   1.0000
  17.500   1.0236   0.11653   0.11204  -0.0011   0.0053   1.0000
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