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EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 682 AIRFOIL (e682-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.73 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e682-il-1000000.txt
Download as CSV file: xf-e682-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 682 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1973   0.08560   0.08311  -0.0842   0.7837   0.0141
 -11.500  -0.2007   0.08062   0.07814  -0.0864   0.7830   0.0143
 -11.250  -0.2073   0.07497   0.07250  -0.0888   0.7822   0.0144
 -11.000  -0.2179   0.06841   0.06595  -0.0918   0.7814   0.0145
 -10.750  -0.2394   0.05907   0.05662  -0.0967   0.7807   0.0145
 -10.500  -0.3283   0.03928   0.03662  -0.1082   0.7799   0.0140
 -10.250  -0.3590   0.03455   0.03174  -0.1073   0.7786   0.0140
 -10.000  -0.3834   0.03104   0.02808  -0.1049   0.7771   0.0140
  -9.750  -0.4005   0.02859   0.02550  -0.1019   0.7755   0.0141
  -9.500  -0.4124   0.02675   0.02355  -0.0983   0.7742   0.0143
  -9.250  -0.4238   0.02481   0.02150  -0.0942   0.7731   0.0144
  -9.000  -0.4296   0.02229   0.01881  -0.0908   0.7721   0.0146
  -8.750  -0.4295   0.02002   0.01636  -0.0880   0.7710   0.0150
  -8.500  -0.4265   0.01777   0.01386  -0.0851   0.7698   0.0159
  -8.250  -0.4138   0.01812   0.01391  -0.0824   0.7684   0.0167
  -8.000  -0.4405   0.02057   0.01522  -0.0801   0.7692   0.0118
  -7.750  -0.4200   0.01898   0.01342  -0.0791   0.7680   0.0119
  -7.500  -0.3972   0.01775   0.01202  -0.0785   0.7669   0.0119
  -7.250  -0.3734   0.01692   0.01107  -0.0781   0.7659   0.0122
  -7.000  -0.3489   0.01617   0.01023  -0.0777   0.7650   0.0124
  -6.750  -0.3240   0.01546   0.00943  -0.0774   0.7641   0.0125
  -6.500  -0.2991   0.01480   0.00870  -0.0771   0.7632   0.0126
  -6.250  -0.2741   0.01430   0.00814  -0.0768   0.7622   0.0128
  -6.000  -0.2493   0.01383   0.00762  -0.0765   0.7611   0.0129
  -5.750  -0.2248   0.01340   0.00714  -0.0762   0.7598   0.0130
  -5.500  -0.2045   0.01249   0.00619  -0.0751   0.7588   0.0134
  -5.250  -0.1821   0.01195   0.00564  -0.0743   0.7580   0.0139
  -5.000  -0.1583   0.01157   0.00525  -0.0738   0.7570   0.0144
  -4.750  -0.1339   0.01124   0.00491  -0.0734   0.7559   0.0148
  -4.500  -0.1091   0.01095   0.00459  -0.0730   0.7546   0.0153
  -4.250  -0.0839   0.01069   0.00431  -0.0727   0.7533   0.0160
  -4.000  -0.0581   0.01048   0.00408  -0.0726   0.7519   0.0166
  -3.750  -0.0328   0.01021   0.00377  -0.0723   0.7505   0.0176
  -3.500  -0.0069   0.00999   0.00355  -0.0721   0.7492   0.0194
  -3.250   0.0196   0.00982   0.00336  -0.0720   0.7478   0.0216
  -3.000   0.0425   0.00938   0.00315  -0.0714   0.7464   0.0730
  -2.750   0.0642   0.00891   0.00302  -0.0707   0.7447   0.1673
  -2.500   0.0846   0.00834   0.00290  -0.0698   0.7432   0.2881
  -2.250   0.1044   0.00767   0.00273  -0.0689   0.7418   0.4275
  -2.000   0.1225   0.00679   0.00250  -0.0677   0.7402   0.6098
  -1.750   0.1433   0.00638   0.00270  -0.0663   0.7384   0.7832
  -1.500   0.1724   0.00649   0.00278  -0.0666   0.7367   0.8029
  -1.250   0.2013   0.00668   0.00294  -0.0668   0.7349   0.8167
  -1.000   0.2292   0.00698   0.00325  -0.0665   0.7332   0.8274
  -0.750   0.2582   0.00710   0.00333  -0.0667   0.7315   0.8329
  -0.500   0.2858   0.00735   0.00359  -0.0665   0.7296   0.8380
  -0.250   0.3138   0.00758   0.00381  -0.0664   0.7278   0.8440
   0.000   0.3413   0.00767   0.00391  -0.0663   0.7260   0.8485
   0.250   0.3678   0.00780   0.00406  -0.0659   0.7237   0.8518
   0.500   0.3952   0.00791   0.00418  -0.0657   0.7213   0.8552
   0.750   0.4237   0.00798   0.00422  -0.0659   0.7188   0.8588
   1.000   0.4536   0.00804   0.00425  -0.0665   0.7163   0.8619
   1.250   0.4805   0.00802   0.00421  -0.0663   0.7135   0.8638
   1.500   0.5074   0.00797   0.00419  -0.0663   0.7109   0.8650
   1.750   0.5352   0.00792   0.00415  -0.0664   0.7077   0.8660
   2.000   0.5635   0.00786   0.00409  -0.0667   0.7043   0.8669
   2.250   0.5921   0.00780   0.00401  -0.0671   0.7010   0.8677
   2.500   0.6205   0.00777   0.00398  -0.0675   0.6974   0.8684
   2.750   0.6483   0.00771   0.00395  -0.0677   0.6931   0.8693
   3.000   0.6766   0.00763   0.00388  -0.0681   0.6885   0.8699
   3.250   0.7051   0.00759   0.00382  -0.0685   0.6840   0.8706
   3.500   0.7328   0.00753   0.00381  -0.0688   0.6777   0.8714
   3.750   0.7607   0.00748   0.00374  -0.0691   0.6708   0.8720
   4.000   0.7884   0.00744   0.00372  -0.0694   0.6613   0.8726
   4.250   0.8154   0.00742   0.00369  -0.0695   0.6498   0.8731
   4.500   0.8415   0.00744   0.00368  -0.0695   0.6348   0.8737
   4.750   0.8658   0.00753   0.00370  -0.0691   0.6156   0.8745
   5.000   0.8888   0.00768   0.00378  -0.0684   0.5949   0.8751
   5.250   0.9106   0.00788   0.00389  -0.0676   0.5726   0.8756
   5.500   0.9312   0.00812   0.00404  -0.0665   0.5502   0.8761
   5.750   0.9512   0.00836   0.00421  -0.0654   0.5278   0.8765
   6.000   0.9687   0.00861   0.00438  -0.0638   0.5034   0.8772
   6.250   0.9828   0.00891   0.00457  -0.0615   0.4757   0.8779
   6.500   0.9914   0.00927   0.00481  -0.0580   0.4448   0.8790
   6.750   0.9935   0.00973   0.00512  -0.0534   0.4095   0.8801
   7.000   1.0004   0.01025   0.00551  -0.0499   0.3800   0.8810
   7.250   1.0073   0.01082   0.00596  -0.0466   0.3509   0.8819
   7.500   1.0146   0.01144   0.00646  -0.0435   0.3231   0.8829
   7.750   1.0243   0.01203   0.00696  -0.0410   0.2998   0.8837
   8.000   1.0319   0.01276   0.00757  -0.0382   0.2720   0.8847
   8.250   1.0406   0.01350   0.00820  -0.0358   0.2468   0.8856
   8.500   1.0484   0.01434   0.00891  -0.0333   0.2199   0.8865
   8.750   1.0573   0.01517   0.00962  -0.0311   0.1951   0.8873
   9.000   1.0659   0.01606   0.01039  -0.0290   0.1694   0.8882
   9.250   1.0756   0.01694   0.01116  -0.0270   0.1479   0.8892
   9.500   1.0842   0.01789   0.01199  -0.0250   0.1251   0.8898
   9.750   1.0943   0.01881   0.01281  -0.0233   0.1050   0.8904
  10.000   1.1008   0.01994   0.01379  -0.0212   0.0806   0.8910
  10.250   1.1079   0.02106   0.01479  -0.0193   0.0603   0.8916
  10.500   1.1154   0.02218   0.01580  -0.0174   0.0427   0.8925
  10.750   1.1171   0.02368   0.01715  -0.0150   0.0209   0.8935
  11.000   1.1242   0.02491   0.01833  -0.0132   0.0125   0.8943
  11.250   1.1372   0.02579   0.01925  -0.0121   0.0113   0.8950
  11.500   1.1484   0.02681   0.02031  -0.0108   0.0101   0.8957
  11.750   1.1594   0.02787   0.02141  -0.0097   0.0096   0.8965
  12.000   1.1712   0.02891   0.02251  -0.0086   0.0092   0.8973
  12.250   1.1838   0.02991   0.02357  -0.0077   0.0090   0.8981
  12.500   1.1942   0.03109   0.02481  -0.0066   0.0085   0.8989
  12.750   1.2045   0.03232   0.02611  -0.0056   0.0082   0.8997
  13.000   1.2143   0.03361   0.02746  -0.0047   0.0080   0.9006
  13.250   1.2219   0.03512   0.02902  -0.0036   0.0077   0.9014
  13.500   1.2301   0.03660   0.03057  -0.0027   0.0076   0.9022
  13.750   1.2336   0.03854   0.03259  -0.0015   0.0073   0.9032
  14.000   1.2362   0.04064   0.03477  -0.0005   0.0072   0.9041
  14.250   1.2345   0.04319   0.03744   0.0007   0.0070   0.9050
  14.500   1.2427   0.04491   0.03922   0.0012   0.0069   0.9056
  14.750   1.2487   0.04686   0.04126   0.0017   0.0068   0.9067
  15.000   1.2524   0.04909   0.04358   0.0022   0.0068   0.9079
  15.250   1.2558   0.05142   0.04599   0.0026   0.0068   0.9090
  15.500   1.2586   0.05388   0.04855   0.0028   0.0066   0.9101
  15.750   1.2611   0.05644   0.05120   0.0030   0.0065   0.9111
  16.000   1.2648   0.05897   0.05381   0.0029   0.0064   0.9123
  16.250   1.2667   0.06176   0.05670   0.0028   0.0062   0.9134
  16.500   1.2680   0.06472   0.05975   0.0025   0.0061   0.9145
  16.750   1.2668   0.06805   0.06318   0.0021   0.0061   0.9156
  17.000   1.2682   0.07114   0.06636   0.0015   0.0060   0.9167
  17.250   1.2671   0.07466   0.06998   0.0007   0.0059   0.9178
  17.500   1.2658   0.07830   0.07371  -0.0002   0.0058   0.9188
  17.750   1.2630   0.08222   0.07773  -0.0013   0.0057   0.9198
  18.000   1.2597   0.08626   0.08186  -0.0025   0.0056   0.9211
  18.250   1.2569   0.09028   0.08599  -0.0038   0.0056   0.9225
  18.500   1.2543   0.09437   0.09018  -0.0053   0.0055   0.9240
  18.750   1.2502   0.09873   0.09464  -0.0069   0.0055   0.9254
  19.000   1.2453   0.10327   0.09927  -0.0088   0.0054   0.9269
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