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E387 (e387-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.58 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e387-il-1000000.txt
Download as CSV file: xf-e387-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E387                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2739   0.08430   0.08284  -0.0309   1.0000   0.0092
  -9.000  -0.2707   0.08091   0.07947  -0.0318   1.0000   0.0094
  -8.750  -0.2687   0.07723   0.07580  -0.0328   1.0000   0.0094
  -8.500  -0.2612   0.07279   0.07136  -0.0357   0.9815   0.0095
  -8.250  -0.2450   0.06713   0.06566  -0.0416   0.9507   0.0098
  -8.000  -0.2395   0.06295   0.06134  -0.0442   0.9003   0.0099
  -7.750  -0.2413   0.05953   0.05779  -0.0448   0.8629   0.0100
  -7.500  -0.2439   0.05599   0.05415  -0.0457   0.8366   0.0101
  -7.250  -0.2478   0.05244   0.05053  -0.0468   0.8143   0.0104
  -7.000  -0.2537   0.04888   0.04692  -0.0484   0.7960   0.0103
  -6.750  -0.2536   0.04410   0.04208  -0.0530   0.7813   0.0105
  -6.500  -0.2493   0.03842   0.03632  -0.0588   0.7690   0.0107
  -6.250  -0.2494   0.04533   0.04302  -0.0747   0.7945   0.0105
  -6.000  -0.2329   0.03899   0.03643  -0.0783   0.7798   0.0111
  -5.750  -0.2112   0.03159   0.02859  -0.0802   0.7676   0.0121
  -5.500  -0.1998   0.02305   0.01929  -0.0819   0.7564   0.0127
  -5.250  -0.1764   0.02149   0.01758  -0.0821   0.7450   0.0132
  -5.000  -0.1518   0.02024   0.01615  -0.0822   0.7346   0.0139
  -4.500  -0.1011   0.01385   0.00869  -0.0811   0.7163   0.0115
  -4.250  -0.0747   0.01247   0.00704  -0.0808   0.7079   0.0112
  -4.000  -0.0476   0.01153   0.00593  -0.0806   0.6994   0.0112
  -3.750  -0.0203   0.01092   0.00519  -0.0804   0.6917   0.0115
  -3.500   0.0068   0.01013   0.00426  -0.0802   0.6840   0.0114
  -3.250   0.0342   0.00950   0.00353  -0.0800   0.6772   0.0113
  -3.000   0.0617   0.00903   0.00296  -0.0798   0.6701   0.0115
  -2.750   0.0896   0.00869   0.00253  -0.0797   0.6637   0.0119
  -2.500   0.1175   0.00829   0.00204  -0.0797   0.6572   0.0129
  -2.250   0.1453   0.00806   0.00173  -0.0796   0.6513   0.0145
  -2.000   0.1736   0.00790   0.00152  -0.0796   0.6451   0.0161
  -1.750   0.2015   0.00764   0.00132  -0.0796   0.6393   0.0387
  -1.500   0.2292   0.00732   0.00120  -0.0796   0.6339   0.1031
  -1.000   0.2846   0.00686   0.00109  -0.0798   0.6227   0.2388
  -0.750   0.3123   0.00655   0.00106  -0.0800   0.6174   0.3406
  -0.500   0.3393   0.00617   0.00107  -0.0800   0.6120   0.4832
  -0.250   0.3659   0.00583   0.00109  -0.0799   0.6069   0.6230
   0.000   0.3915   0.00547   0.00113  -0.0794   0.6017   0.7634
   0.250   0.4124   0.00505   0.00116  -0.0774   0.5967   0.9460
   0.500   0.4530   0.00505   0.00113  -0.0802   0.5914   1.0000
   0.750   0.4808   0.00510   0.00113  -0.0802   0.5861   1.0000
   1.000   0.5085   0.00518   0.00114  -0.0801   0.5808   1.0000
   1.250   0.5365   0.00522   0.00116  -0.0801   0.5754   1.0000
   1.500   0.5643   0.00528   0.00118  -0.0801   0.5693   1.0000
   1.750   0.5921   0.00536   0.00122  -0.0800   0.5633   1.0000
   2.000   0.6200   0.00541   0.00125  -0.0800   0.5565   1.0000
   2.250   0.6476   0.00550   0.00129  -0.0800   0.5497   1.0000
   2.500   0.6756   0.00556   0.00134  -0.0800   0.5423   1.0000
   2.750   0.7032   0.00565   0.00140  -0.0800   0.5353   1.0000
   3.000   0.7310   0.00571   0.00146  -0.0800   0.5277   1.0000
   3.250   0.7586   0.00581   0.00152  -0.0799   0.5202   1.0000
   3.500   0.7863   0.00589   0.00159  -0.0799   0.5115   1.0000
   3.750   0.8139   0.00598   0.00169  -0.0799   0.5028   1.0000
   4.000   0.8412   0.00610   0.00178  -0.0798   0.4931   1.0000
   4.250   0.8686   0.00621   0.00187  -0.0798   0.4815   1.0000
   4.500   0.8955   0.00637   0.00198  -0.0797   0.4649   1.0000
   4.750   0.9218   0.00659   0.00212  -0.0795   0.4383   1.0000
   5.000   0.9477   0.00686   0.00228  -0.0792   0.4078   1.0000
   5.250   0.9729   0.00721   0.00249  -0.0789   0.3712   1.0000
   5.500   0.9963   0.00778   0.00280  -0.0784   0.3159   1.0000
   5.750   1.0177   0.00858   0.00327  -0.0776   0.2473   1.0000
   6.000   1.0387   0.00942   0.00377  -0.0768   0.1837   1.0000
   6.250   1.0598   0.01021   0.00428  -0.0760   0.1300   1.0000
   6.500   1.0799   0.01108   0.00486  -0.0751   0.0775   1.0000
   6.750   1.0978   0.01219   0.00563  -0.0738   0.0237   1.0000
   7.000   1.1198   0.01281   0.00619  -0.0730   0.0127   1.0000
   7.250   1.1427   0.01330   0.00671  -0.0723   0.0107   1.0000
   7.500   1.1655   0.01380   0.00727  -0.0716   0.0099   1.0000
   7.750   1.1880   0.01428   0.00782  -0.0709   0.0095   1.0000
   8.000   1.2098   0.01482   0.00842  -0.0700   0.0091   1.0000
   8.250   1.2309   0.01540   0.00906  -0.0691   0.0088   1.0000
   8.500   1.2510   0.01604   0.00975  -0.0681   0.0085   1.0000
   8.750   1.2700   0.01672   0.01050  -0.0669   0.0083   1.0000
   9.000   1.2877   0.01748   0.01133  -0.0655   0.0079   1.0000
   9.250   1.3032   0.01836   0.01229  -0.0638   0.0077   1.0000
   9.500   1.3131   0.01958   0.01359  -0.0614   0.0074   1.0000
   9.750   1.3162   0.02099   0.01512  -0.0579   0.0072   1.0000
  10.000   1.3212   0.02210   0.01631  -0.0548   0.0072   1.0000
  10.250   1.3169   0.02405   0.01837  -0.0508   0.0070   1.0000
  10.500   1.3263   0.02510   0.01951  -0.0489   0.0070   1.0000
  10.750   1.3369   0.02612   0.02060  -0.0472   0.0068   1.0000
  11.000   1.3464   0.02728   0.02185  -0.0456   0.0067   1.0000
  11.250   1.3529   0.02882   0.02349  -0.0439   0.0066   1.0000
  11.500   1.3587   0.03056   0.02532  -0.0423   0.0065   1.0000
  11.750   1.3648   0.03232   0.02719  -0.0409   0.0065   1.0000
  12.000   1.3710   0.03413   0.02910  -0.0397   0.0064   1.0000
  12.250   1.3750   0.03641   0.03151  -0.0384   0.0064   1.0000
  12.500   1.3797   0.03854   0.03375  -0.0373   0.0063   1.0000
  12.750   1.3835   0.04084   0.03618  -0.0364   0.0062   1.0000
  13.000   1.3856   0.04342   0.03891  -0.0356   0.0062   1.0000
  13.250   1.3867   0.04610   0.04173  -0.0350   0.0061   1.0000
  13.500   1.3866   0.04898   0.04474  -0.0346   0.0060   1.0000
  13.750   1.3824   0.05260   0.04855  -0.0343   0.0061   1.0000
  14.000   1.3796   0.05590   0.05200  -0.0344   0.0060   1.0000
  14.250   1.3697   0.06052   0.05683  -0.0347   0.0061   1.0000
  14.500   1.3641   0.06439   0.06083  -0.0355   0.0060   1.0000
  14.750   1.3539   0.06920   0.06582  -0.0366   0.0059   1.0000
  15.000   1.3433   0.07431   0.07109  -0.0382   0.0059   1.0000
  15.250   1.3305   0.08005   0.07701  -0.0403   0.0059   1.0000
  15.500   1.3141   0.08672   0.08387  -0.0430   0.0059   1.0000
  15.750   1.2981   0.09370   0.09102  -0.0463   0.0059   1.0000
  16.000   1.2835   0.10077   0.09824  -0.0499   0.0059   1.0000
  16.250   1.2641   0.10921   0.10686  -0.0545   0.0059   1.0000
  16.500   1.2430   0.11858   0.11641  -0.0599   0.0060   1.0000
  16.750   1.2216   0.12859   0.12658  -0.0660   0.0061   1.0000
  17.000   1.2000   0.13925   0.13740  -0.0727   0.0062   1.0000
  17.250   1.1783   0.15072   0.14900  -0.0800   0.0063   1.0000
  17.500   1.1542   0.16377   0.16218  -0.0883   0.0065   1.0000
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