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EPPLER 331 AIRFOIL (e331-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 331 AIRFOIL (e331-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.07 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e331-il-1000000.txt
Download as CSV file: xf-e331-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 331 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4701   0.08432   0.08281  -0.0112   1.0000   0.0067
  -8.750  -0.4767   0.07907   0.07759  -0.0160   1.0000   0.0067
  -8.500  -0.4856   0.07472   0.07322  -0.0185   1.0000   0.0067
  -8.250  -0.4982   0.07073   0.06920  -0.0187   1.0000   0.0067
  -8.000  -0.5089   0.06752   0.06595  -0.0171   1.0000   0.0067
  -7.750  -0.5134   0.06375   0.06212  -0.0162   1.0000   0.0067
  -7.500  -0.4951   0.05759   0.05556  -0.0207   0.8692   0.0067
  -7.250  -0.4965   0.05441   0.05206  -0.0182   0.8089   0.0067
  -7.000  -0.5070   0.04986   0.04726  -0.0154   0.7775   0.0069
  -6.750  -0.5014   0.04716   0.04435  -0.0135   0.7507   0.0070
  -6.500  -0.4930   0.04455   0.04155  -0.0117   0.7287   0.0071
  -6.000  -0.4709   0.03935   0.03594  -0.0079   0.6905   0.0073
  -5.750  -0.4581   0.03660   0.03297  -0.0059   0.6749   0.0076
  -5.500  -0.4442   0.03370   0.02983  -0.0036   0.6605   0.0079
  -5.250  -0.4292   0.03050   0.02635  -0.0010   0.6471   0.0083
  -5.000  -0.4112   0.02629   0.02154   0.0032   0.6354   0.0091
  -4.750  -0.3996   0.02254   0.01748   0.0057   0.6233   0.0095
  -4.500  -0.3785   0.02133   0.01612   0.0068   0.6096   0.0097
  -4.250  -0.3565   0.02004   0.01462   0.0080   0.5967   0.0102
  -4.000  -0.3319   0.01416   0.00778   0.0116   0.5876   0.0069
  -3.750  -0.3063   0.01307   0.00654   0.0122   0.5756   0.0071
  -3.500  -0.2807   0.01263   0.00606   0.0127   0.5632   0.0076
  -3.000  -0.2299   0.01150   0.00474   0.0140   0.5408   0.0079
  -2.750  -0.2049   0.01106   0.00421   0.0147   0.5304   0.0082
  -2.250  -0.1534   0.01056   0.00358   0.0159   0.5093   0.0090
  -2.000  -0.1293   0.01012   0.00307   0.0168   0.5001   0.0092
  -1.750  -0.1048   0.00975   0.00264   0.0176   0.4908   0.0095
  -1.500  -0.0794   0.00949   0.00233   0.0183   0.4821   0.0099
  -1.000  -0.0296   0.00891   0.00180   0.0198   0.4650   0.0463
  -0.750  -0.0062   0.00856   0.00169   0.0206   0.4569   0.1295
  -0.500   0.0040   0.00721   0.00147   0.0237   0.4507   0.4757
  -0.250  -0.0006   0.00574   0.00141   0.0307   0.4449   0.8573
   0.000   0.0212   0.00602   0.00175   0.0328   0.4380   0.9140
   0.250   0.0478   0.00640   0.00212   0.0338   0.4307   0.9308
   0.500   0.0779   0.00673   0.00238   0.0338   0.4236   0.9386
   0.750   0.1146   0.00712   0.00271   0.0325   0.4159   0.9455
   1.000   0.1683   0.00757   0.00307   0.0273   0.4078   0.9480
   1.250   0.2168   0.00782   0.00324   0.0230   0.3999   0.9492
   1.500   0.2467   0.00788   0.00324   0.0226   0.3938   0.9505
   1.750   0.2740   0.00790   0.00323   0.0227   0.3882   0.9522
   2.000   0.2775   0.00789   0.00319   0.0279   0.3839   0.9577
   2.250   0.3094   0.00792   0.00317   0.0270   0.3780   0.9581
   2.500   0.3415   0.00794   0.00317   0.0260   0.3724   0.9585
   2.750   0.3726   0.00800   0.00317   0.0252   0.3665   0.9589
   3.000   0.4033   0.00803   0.00318   0.0245   0.3617   0.9594
   3.250   0.4341   0.00806   0.00319   0.0237   0.3561   0.9599
   3.500   0.4642   0.00814   0.00323   0.0231   0.3503   0.9605
   3.750   0.4937   0.00817   0.00325   0.0227   0.3455   0.9611
   4.000   0.5231   0.00822   0.00329   0.0222   0.3402   0.9618
   4.250   0.5519   0.00832   0.00334   0.0219   0.3342   0.9626
   4.500   0.5803   0.00834   0.00339   0.0216   0.3296   0.9634
   4.750   0.6073   0.00840   0.00343   0.0216   0.3241   0.9644
   5.000   0.6332   0.00848   0.00350   0.0219   0.3187   0.9654
   5.250   0.6591   0.00852   0.00356   0.0222   0.3137   0.9668
   5.500   0.6794   0.00859   0.00362   0.0236   0.3084   0.9688
   5.750   0.6921   0.00865   0.00367   0.0268   0.3036   0.9714
   6.000   0.7222   0.00869   0.00373   0.0261   0.2978   0.9718
   6.250   0.7516   0.00881   0.00383   0.0255   0.2905   0.9722
   6.500   0.7815   0.00887   0.00392   0.0248   0.2850   0.9726
   6.750   0.8113   0.00900   0.00403   0.0241   0.2771   0.9731
   7.000   0.8412   0.00910   0.00416   0.0234   0.2702   0.9736
   7.250   0.8699   0.00925   0.00430   0.0229   0.2621   0.9742
   7.500   0.8982   0.00937   0.00444   0.0225   0.2543   0.9749
   7.750   0.9256   0.00955   0.00460   0.0223   0.2452   0.9756
   8.000   0.9528   0.00971   0.00477   0.0221   0.2358   0.9764
   8.250   0.9793   0.00990   0.00496   0.0220   0.2259   0.9774
   8.500   1.0046   0.01014   0.00518   0.0221   0.2140   0.9785
   8.750   1.0285   0.01040   0.00542   0.0225   0.2019   0.9798
   9.000   1.0493   0.01069   0.00568   0.0235   0.1890   0.9816
   9.250   1.0683   0.01102   0.00597   0.0249   0.1747   0.9836
   9.500   1.0962   0.01145   0.00634   0.0242   0.1556   0.9842
   9.750   1.1228   0.01196   0.00678   0.0236   0.1371   0.9849
  10.000   1.1484   0.01252   0.00726   0.0232   0.1181   0.9857
  10.250   1.1720   0.01326   0.00788   0.0230   0.0960   0.9867
  10.500   1.1955   0.01393   0.00847   0.0228   0.0791   0.9879
  10.750   1.2183   0.01458   0.00908   0.0228   0.0667   0.9893
  11.000   1.2382   0.01539   0.00980   0.0231   0.0527   0.9911
  11.250   1.2579   0.01606   0.01045   0.0237   0.0445   0.9930
  11.500   1.2789   0.01681   0.01118   0.0237   0.0364   0.9944
  11.750   1.3029   0.01755   0.01193   0.0231   0.0307   0.9955
  12.000   1.3256   0.01837   0.01277   0.0226   0.0254   0.9970
  12.250   1.3477   0.01925   0.01366   0.0221   0.0214   0.9986
  12.500   1.3682   0.02018   0.01463   0.0217   0.0184   1.0000
  12.750   1.3435   0.02053   0.01505   0.0306   0.0181   1.0000
  13.000   1.3249   0.02120   0.01576   0.0374   0.0174   1.0000
  13.250   1.3166   0.02247   0.01706   0.0411   0.0156   1.0000
  13.500   1.3160   0.02396   0.01864   0.0428   0.0148   1.0000
  13.750   1.3153   0.02586   0.02059   0.0438   0.0132   1.0000
  14.000   1.3142   0.02810   0.02290   0.0442   0.0119   1.0000
  14.250   1.3148   0.03040   0.02528   0.0441   0.0109   1.0000
  14.500   1.3115   0.03324   0.02818   0.0439   0.0098   1.0000
  14.750   1.3080   0.03622   0.03126   0.0434   0.0094   1.0000
  15.000   1.3050   0.03920   0.03432   0.0429   0.0087   1.0000
  15.250   1.2990   0.04256   0.03777   0.0422   0.0082   1.0000
  15.500   1.2918   0.04612   0.04141   0.0414   0.0079   1.0000
  15.750   1.2815   0.05009   0.04546   0.0404   0.0074   1.0000
  16.000   1.2757   0.05354   0.04899   0.0395   0.0067   1.0000
  16.250   1.2666   0.05748   0.05301   0.0384   0.0064   1.0000
  16.500   1.2574   0.06157   0.05718   0.0371   0.0059   1.0000
  16.750   1.2459   0.06612   0.06182   0.0356   0.0055   1.0000
  17.000   1.2367   0.07041   0.06616   0.0341   0.0046   1.0000
  17.250   1.2246   0.07520   0.07109   0.0325   0.0054   1.0000
  17.500   1.2201   0.07897   0.07492   0.0312   0.0048   1.0000
  17.750   1.2088   0.08377   0.07980   0.0294   0.0045   1.0000
  18.000   1.2000   0.08830   0.08441   0.0277   0.0042   1.0000
  18.250   1.1873   0.09349   0.08968   0.0257   0.0040   1.0000
  18.500   1.1780   0.09820   0.09446   0.0239   0.0034   1.0000
  18.750   1.1672   0.10326   0.09963   0.0218   0.0038   1.0000
  19.000   1.1584   0.10807   0.10450   0.0199   0.0033   1.0000
  19.250   1.1484   0.11313   0.10965   0.0177   0.0033   1.0000
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