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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.9 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e201-il-1000000.txt
Download as CSV file: xf-e201-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E201  (11.88%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4372   0.08320   0.08163  -0.0454   1.0000   0.0150
 -10.000  -0.4408   0.07931   0.07775  -0.0469   1.0000   0.0152
  -9.750  -0.4646   0.07077   0.06926  -0.0508   1.0000   0.0152
  -9.250  -0.6043   0.02611   0.02268  -0.0820   0.9852   0.0107
  -9.000  -0.5829   0.02292   0.01919  -0.0835   0.9804   0.0109
  -8.750  -0.5558   0.02100   0.01710  -0.0850   0.9757   0.0112
  -8.500  -0.5262   0.01915   0.01504  -0.0865   0.9716   0.0114
  -8.250  -0.5033   0.01776   0.01349  -0.0863   0.9611   0.0115
  -8.000  -0.4765   0.01670   0.01230  -0.0866   0.9499   0.0118
  -7.750  -0.4494   0.01567   0.01113  -0.0869   0.9347   0.0121
  -7.250  -0.3998   0.01404   0.00915  -0.0861   0.8901   0.0125
  -7.000  -0.3765   0.01341   0.00835  -0.0853   0.8674   0.0128
  -6.750  -0.3533   0.01279   0.00758  -0.0845   0.8466   0.0130
  -6.500  -0.3296   0.01226   0.00690  -0.0838   0.8277   0.0132
  -6.250  -0.3056   0.01176   0.00625  -0.0831   0.8103   0.0134
  -6.000  -0.2811   0.01130   0.00567  -0.0825   0.7945   0.0136
  -5.750  -0.2558   0.01097   0.00523  -0.0821   0.7801   0.0139
  -5.250  -0.2063   0.00993   0.00395  -0.0811   0.7541   0.0150
  -5.000  -0.1804   0.00958   0.00351  -0.0807   0.7428   0.0157
  -4.750  -0.1540   0.00933   0.00317  -0.0804   0.7325   0.0165
  -4.500  -0.1273   0.00912   0.00288  -0.0802   0.7223   0.0174
  -4.250  -0.1002   0.00893   0.00262  -0.0800   0.7130   0.0182
  -4.000  -0.0733   0.00873   0.00235  -0.0798   0.7046   0.0201
  -3.750  -0.0463   0.00849   0.00211  -0.0797   0.6961   0.0278
  -3.500  -0.0204   0.00807   0.00188  -0.0795   0.6885   0.0770
  -3.250   0.0063   0.00778   0.00172  -0.0794   0.6810   0.1192
  -3.000   0.0331   0.00755   0.00160  -0.0793   0.6742   0.1608
  -2.750   0.0601   0.00730   0.00149  -0.0792   0.6672   0.2071
  -2.500   0.0869   0.00709   0.00139  -0.0792   0.6608   0.2566
  -2.250   0.1138   0.00681   0.00132  -0.0791   0.6546   0.3221
  -2.000   0.1405   0.00661   0.00127  -0.0790   0.6484   0.3864
  -1.750   0.1681   0.00649   0.00125  -0.0790   0.6427   0.4291
  -1.500   0.1958   0.00641   0.00123  -0.0790   0.6369   0.4613
  -1.250   0.2232   0.00635   0.00122  -0.0789   0.6314   0.4946
  -1.000   0.2512   0.00628   0.00121  -0.0789   0.6259   0.5211
  -0.750   0.2789   0.00625   0.00120  -0.0789   0.6204   0.5425
  -0.250   0.3346   0.00617   0.00121  -0.0789   0.6100   0.5902
   0.000   0.3621   0.00615   0.00122  -0.0788   0.6047   0.6168
   0.250   0.3897   0.00610   0.00125  -0.0788   0.5999   0.6458
   0.500   0.4173   0.00604   0.00127  -0.0787   0.5946   0.6780
   0.750   0.4442   0.00600   0.00131  -0.0785   0.5895   0.7148
   1.000   0.4711   0.00593   0.00136  -0.0783   0.5846   0.7558
   1.250   0.4975   0.00584   0.00140  -0.0779   0.5793   0.8011
   1.500   0.5225   0.00578   0.00147  -0.0772   0.5740   0.8522
   1.750   0.5463   0.00568   0.00153  -0.0760   0.5685   0.9123
   2.000   0.5781   0.00568   0.00158  -0.0767   0.5618   0.9637
   2.250   0.6183   0.00573   0.00162  -0.0794   0.5551   0.9860
   2.500   0.6585   0.00579   0.00166  -0.0822   0.5478   0.9967
   2.750   0.6894   0.00586   0.00170  -0.0829   0.5406   1.0000
   3.000   0.7146   0.00593   0.00176  -0.0824   0.5329   1.0000
   3.250   0.7400   0.00602   0.00182  -0.0819   0.5259   1.0000
   3.500   0.7657   0.00610   0.00189  -0.0815   0.5180   1.0000
   3.750   0.7916   0.00619   0.00196  -0.0811   0.5105   1.0000
   4.000   0.8174   0.00630   0.00205  -0.0807   0.5014   1.0000
   4.250   0.8437   0.00639   0.00214  -0.0804   0.4919   1.0000
   4.500   0.8696   0.00651   0.00224  -0.0801   0.4822   1.0000
   4.750   0.8955   0.00664   0.00235  -0.0798   0.4716   1.0000
   5.000   0.9214   0.00678   0.00247  -0.0794   0.4582   1.0000
   5.250   0.9460   0.00700   0.00260  -0.0789   0.4327   1.0000
   5.500   0.9702   0.00726   0.00277  -0.0783   0.4072   1.0000
   5.750   0.9932   0.00762   0.00300  -0.0775   0.3724   1.0000
   6.000   1.0135   0.00819   0.00332  -0.0763   0.3208   1.0000
   6.250   1.0324   0.00888   0.00373  -0.0749   0.2659   1.0000
   6.500   1.0510   0.00957   0.00417  -0.0736   0.2159   1.0000
   6.750   1.0699   0.01023   0.00462  -0.0722   0.1739   1.0000
   7.000   1.0890   0.01086   0.00506  -0.0709   0.1388   1.0000
   7.250   1.1073   0.01152   0.00553  -0.0695   0.1052   1.0000
   7.500   1.1252   0.01218   0.00602  -0.0680   0.0771   1.0000
   7.750   1.1423   0.01286   0.00656  -0.0664   0.0515   1.0000
   8.000   1.1562   0.01371   0.00723  -0.0642   0.0252   1.0000
   8.250   1.1703   0.01452   0.00794  -0.0621   0.0116   1.0000
   8.500   1.1889   0.01500   0.00845  -0.0606   0.0102   1.0000
   8.750   1.2061   0.01553   0.00901  -0.0590   0.0093   1.0000
   9.000   1.2197   0.01611   0.00963  -0.0566   0.0085   1.0000
   9.250   1.2307   0.01677   0.01037  -0.0539   0.0081   1.0000
   9.500   1.2445   0.01731   0.01095  -0.0517   0.0079   1.0000
   9.750   1.2569   0.01794   0.01164  -0.0494   0.0077   1.0000
  10.000   1.2689   0.01861   0.01236  -0.0472   0.0074   1.0000
  10.250   1.2791   0.01940   0.01323  -0.0448   0.0073   1.0000
  10.500   1.2889   0.02025   0.01413  -0.0426   0.0070   1.0000
  10.750   1.2975   0.02121   0.01515  -0.0403   0.0068   1.0000
  11.000   1.3049   0.02229   0.01631  -0.0381   0.0066   1.0000
  11.250   1.3119   0.02347   0.01756  -0.0361   0.0065   1.0000
  11.500   1.3137   0.02509   0.01926  -0.0338   0.0062   1.0000
  11.750   1.3191   0.02656   0.02080  -0.0321   0.0062   1.0000
  12.000   1.3143   0.02892   0.02328  -0.0298   0.0060   1.0000
  12.250   1.3084   0.03156   0.02604  -0.0279   0.0058   1.0000
  12.500   1.3132   0.03340   0.02796  -0.0268   0.0057   1.0000
  12.750   1.3181   0.03529   0.02992  -0.0259   0.0057   1.0000
  13.000   1.3215   0.03738   0.03210  -0.0250   0.0057   1.0000
  13.250   1.3250   0.03952   0.03432  -0.0243   0.0056   1.0000
  13.500   1.3288   0.04169   0.03659  -0.0237   0.0055   1.0000
  13.750   1.3304   0.04414   0.03913  -0.0232   0.0055   1.0000
  14.000   1.3318   0.04668   0.04177  -0.0227   0.0055   1.0000
  14.250   1.3340   0.04921   0.04439  -0.0225   0.0054   1.0000
  14.500   1.3320   0.05229   0.04757  -0.0222   0.0054   1.0000
  14.750   1.3344   0.05497   0.05034  -0.0223   0.0054   1.0000
  15.000   1.3327   0.05820   0.05368  -0.0224   0.0054   1.0000
  15.250   1.3320   0.06142   0.05701  -0.0227   0.0053   1.0000
  15.500   1.3322   0.06464   0.06033  -0.0233   0.0053   1.0000
  15.750   1.3295   0.06832   0.06412  -0.0239   0.0052   1.0000
  16.000   1.3262   0.07220   0.06812  -0.0247   0.0052   1.0000
  16.250   1.3223   0.07629   0.07234  -0.0258   0.0052   1.0000
  16.500   1.3175   0.08067   0.07684  -0.0271   0.0051   1.0000
  16.750   1.3111   0.08539   0.08169  -0.0287   0.0052   1.0000
  17.000   1.3047   0.09028   0.08673  -0.0305   0.0051   1.0000
  17.250   1.2967   0.09562   0.09220  -0.0327   0.0051   1.0000
  17.500   1.2880   0.10125   0.09796  -0.0352   0.0051   1.0000
  17.750   1.2767   0.10746   0.10432  -0.0381   0.0051   1.0000
  18.000   1.2699   0.11305   0.11003  -0.0410   0.0050   1.0000
  18.250   1.2590   0.11961   0.11673  -0.0445   0.0050   1.0000
  18.500   1.2420   0.12756   0.12485  -0.0488   0.0051   1.0000
  18.750   1.2321   0.13430   0.13171  -0.0528   0.0050   1.0000
  19.000   1.2144   0.14294   0.14052  -0.0579   0.0051   1.0000
  19.250   1.2004   0.15105   0.14877  -0.0629   0.0051   1.0000
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