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E220 (11.48%) (e220-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E220 (11.48%) (e220-il)
Reynolds number: 50,000
Max Cl/Cd: 31.02 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e220-il-50000-n5.txt
Download as CSV file: xf-e220-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E220  (11.48%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4449   0.09955   0.09318  -0.0251   1.0000   0.0434
  -9.500  -0.4444   0.09505   0.08875  -0.0276   1.0000   0.0427
  -9.250  -0.4452   0.09034   0.08413  -0.0305   1.0000   0.0420
  -9.000  -0.4483   0.08514   0.07901  -0.0342   1.0000   0.0414
  -8.750  -0.4538   0.07947   0.07343  -0.0390   1.0000   0.0406
  -8.500  -0.4634   0.07411   0.06813  -0.0429   1.0000   0.0399
  -8.250  -0.4758   0.06960   0.06365  -0.0446   1.0000   0.0393
  -8.000  -0.4883   0.06527   0.05927  -0.0454   1.0000   0.0388
  -7.750  -0.5026   0.06215   0.05610  -0.0441   1.0000   0.0384
  -7.500  -0.5105   0.05848   0.05222  -0.0437   0.9869   0.0380
  -7.250  -0.4991   0.05336   0.04666  -0.0464   0.9697   0.0380
  -7.000  -0.4834   0.04935   0.04221  -0.0481   0.9561   0.0392
  -6.750  -0.4662   0.04571   0.03807  -0.0491   0.9442   0.0409
  -6.500  -0.4487   0.04239   0.03417  -0.0491   0.9329   0.0427
  -6.250  -0.4289   0.03923   0.03037  -0.0488   0.9232   0.0443
  -6.000  -0.4042   0.03630   0.02676  -0.0486   0.9154   0.0457
  -5.750  -0.3809   0.03390   0.02403  -0.0482   0.9068   0.0476
  -5.500  -0.3536   0.03225   0.02213  -0.0486   0.9001   0.0534
  -5.250  -0.3277   0.03062   0.02007  -0.0480   0.8921   0.0590
  -5.000  -0.2987   0.02901   0.01839  -0.0483   0.8864   0.0670
  -4.750  -0.2740   0.02781   0.01707  -0.0477   0.8788   0.0790
  -4.500  -0.2450   0.02656   0.01567  -0.0478   0.8731   0.0962
  -4.000  -0.1960   0.02425   0.01369  -0.0473   0.8602   0.1870
  -3.750  -0.1761   0.02315   0.01313  -0.0464   0.8540   0.2900
  -3.500  -0.1610   0.02224   0.01285  -0.0443   0.8473   0.4235
  -3.250  -0.1389   0.02133   0.01274  -0.0422   0.8429   0.6069
  -3.000  -0.0457   0.02117   0.01278  -0.0509   0.8426   0.8385
  -2.750   0.0098   0.02161   0.01282  -0.0549   0.8381   0.9055
  -2.500   0.0659   0.02185   0.01263  -0.0600   0.8340   0.9520
  -2.250   0.1296   0.02171   0.01209  -0.0672   0.8307   0.9861
  -2.000   0.1727   0.02154   0.01160  -0.0711   0.8255   1.0000
  -1.750   0.1915   0.02167   0.01155  -0.0704   0.8187   1.0000
  -1.500   0.2113   0.02181   0.01149  -0.0695   0.8129   1.0000
  -1.250   0.2300   0.02205   0.01159  -0.0687   0.8059   1.0000
  -1.000   0.2508   0.02222   0.01157  -0.0678   0.8007   1.0000
  -0.750   0.2698   0.02255   0.01179  -0.0671   0.7938   1.0000
  -0.500   0.2907   0.02280   0.01191  -0.0662   0.7881   1.0000
  -0.250   0.3104   0.02314   0.01215  -0.0653   0.7821   1.0000
   0.000   0.3300   0.02349   0.01240  -0.0644   0.7757   1.0000
   0.250   0.3519   0.02374   0.01255  -0.0634   0.7708   1.0000
   0.500   0.3691   0.02425   0.01302  -0.0624   0.7634   1.0000
   0.750   0.3908   0.02453   0.01323  -0.0614   0.7581   1.0000
   1.000   0.4081   0.02507   0.01373  -0.0602   0.7508   1.0000
   1.250   0.4291   0.02541   0.01403  -0.0591   0.7449   1.0000
   1.500   0.4472   0.02590   0.01451  -0.0579   0.7379   1.0000
   1.750   0.4672   0.02630   0.01489  -0.0567   0.7311   1.0000
   2.000   0.4861   0.02676   0.01536  -0.0554   0.7242   1.0000
   2.250   0.5054   0.02719   0.01579  -0.0541   0.7169   1.0000
   2.500   0.5241   0.02765   0.01627  -0.0528   0.7095   1.0000
   2.750   0.5438   0.02806   0.01670  -0.0515   0.7020   1.0000
   3.000   0.5612   0.02859   0.01729  -0.0500   0.6937   1.0000
   3.250   0.5831   0.02887   0.01762  -0.0488   0.6865   1.0000
   3.500   0.5985   0.02948   0.01828  -0.0471   0.6769   1.0000
   3.750   0.6240   0.02952   0.01841  -0.0461   0.6705   1.0000
   4.000   0.6380   0.03018   0.01915  -0.0442   0.6596   1.0000
   4.250   0.6563   0.03057   0.01963  -0.0426   0.6501   1.0000
   4.500   0.6809   0.03057   0.01972  -0.0414   0.6422   1.0000
   4.750   0.6958   0.03111   0.02037  -0.0394   0.6305   1.0000
   5.000   0.7133   0.03147   0.02087  -0.0377   0.6195   1.0000
   5.250   0.7378   0.03135   0.02088  -0.0363   0.6103   1.0000
   5.500   0.7587   0.03138   0.02105  -0.0346   0.5991   1.0000
   5.750   0.7756   0.03161   0.02142  -0.0326   0.5859   1.0000
   6.000   0.7934   0.03172   0.02173  -0.0306   0.5725   1.0000
   6.250   0.8122   0.03171   0.02188  -0.0286   0.5586   1.0000
   6.500   0.8318   0.03157   0.02190  -0.0266   0.5441   1.0000
   6.750   0.8528   0.03125   0.02176  -0.0245   0.5287   1.0000
   7.000   0.8694   0.03117   0.02185  -0.0222   0.5107   1.0000
   7.250   0.8840   0.03120   0.02208  -0.0196   0.4905   1.0000
   7.500   0.9047   0.03074   0.02177  -0.0174   0.4693   1.0000
   7.750   0.9212   0.03060   0.02174  -0.0148   0.4439   1.0000
   8.000   0.9381   0.03047   0.02165  -0.0123   0.4149   1.0000
   8.250   0.9514   0.03067   0.02181  -0.0095   0.3829   1.0000
   8.500   0.9608   0.03120   0.02225  -0.0066   0.3495   1.0000
   8.750   0.9657   0.03208   0.02298  -0.0034   0.3175   1.0000
   9.000   0.9661   0.03327   0.02408  -0.0001   0.2887   1.0000
   9.250   0.9653   0.03472   0.02541   0.0027   0.2612   1.0000
   9.500   0.9649   0.03637   0.02695   0.0052   0.2355   1.0000
   9.750   0.9645   0.03816   0.02863   0.0073   0.2118   1.0000
  10.000   0.9645   0.04008   0.03047   0.0092   0.1901   1.0000
  10.250   0.9648   0.04212   0.03243   0.0108   0.1699   1.0000
  10.500   0.9649   0.04428   0.03452   0.0123   0.1510   1.0000
  10.750   0.9656   0.04650   0.03667   0.0136   0.1350   1.0000
  11.000   0.9656   0.04883   0.03893   0.0147   0.1203   1.0000
  11.250   0.9669   0.05119   0.04128   0.0157   0.1072   1.0000
  11.500   0.9692   0.05358   0.04372   0.0166   0.0957   1.0000
  11.750   0.9728   0.05599   0.04626   0.0175   0.0858   1.0000
  12.000   0.9761   0.05844   0.04875   0.0183   0.0780   1.0000
  12.250   0.9799   0.06094   0.05135   0.0190   0.0710   1.0000
  12.500   0.9889   0.06331   0.05386   0.0200   0.0657   1.0000
  12.750   0.9926   0.06611   0.05688   0.0206   0.0607   1.0000
  13.000   0.9976   0.06859   0.05928   0.0211   0.0566   1.0000
  13.250   0.9958   0.07237   0.06347   0.0211   0.0536   1.0000
  13.500   0.9940   0.07626   0.06766   0.0210   0.0516   1.0000
  13.750   0.9894   0.08047   0.07212   0.0206   0.0502   1.0000
  14.000   0.9814   0.08509   0.07696   0.0196   0.0490   1.0000
  14.250   0.9710   0.09015   0.08222   0.0181   0.0482   1.0000
  14.500   0.9602   0.09536   0.08756   0.0163   0.0472   1.0000
  14.750   0.9486   0.10095   0.09329   0.0141   0.0464   1.0000
  15.000   0.9037   0.11425   0.10697   0.0063   0.0489   1.0000
  15.250   0.8633   0.12874   0.12158  -0.0023   0.0507   1.0000
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