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E220 (11.48%) (e220-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E220 (11.48%) (e220-il)
Reynolds number: 100,000
Max Cl/Cd: 52.75 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e220-il-100000.txt
Download as CSV file: xf-e220-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4433   0.11771   0.11316  -0.0110   1.0000   0.0905
 -10.250  -0.4565   0.11472   0.11026  -0.0166   1.0000   0.0940
 -10.000  -0.4766   0.11161   0.10729  -0.0237   1.0000   0.0947
  -9.750  -0.4391   0.10595   0.10157  -0.0177   1.0000   0.0981
  -9.500  -0.4308   0.10248   0.09814  -0.0185   1.0000   0.1018
  -9.250  -0.4361   0.09887   0.09461  -0.0224   1.0000   0.1066
  -9.000  -0.4689   0.09474   0.09068  -0.0335   1.0000   0.1085
  -8.750  -0.4297   0.09074   0.08662  -0.0261   1.0000   0.1131
  -8.500  -0.4279   0.08725   0.08321  -0.0287   1.0000   0.1191
  -8.250  -0.4480   0.08269   0.07879  -0.0370   1.0000   0.1215
  -8.000  -0.4381   0.07889   0.07507  -0.0365   1.0000   0.1268
  -7.750  -0.3418   0.06670   0.06315  -0.0412   0.9854   0.1455
  -7.500  -0.4629   0.07471   0.07101  -0.0368   0.9908   0.1324
  -7.250  -0.4475   0.06941   0.06563  -0.0433   0.9797   0.1425
  -7.000  -0.4336   0.06414   0.06020  -0.0501   0.9694   0.1546
  -6.500  -0.3818   0.02961   0.02444  -0.0616   0.9321   0.0831
  -6.250  -0.4096   0.03993   0.03364  -0.0566   0.9364   0.0656
  -6.000  -0.3882   0.03577   0.02905  -0.0565   0.9300   0.0613
  -5.750  -0.3739   0.03234   0.02483  -0.0539   0.9211   0.0576
  -5.500  -0.3474   0.02967   0.02155  -0.0533   0.9155   0.0570
  -5.250  -0.3258   0.02789   0.01952  -0.0523   0.9082   0.0587
  -5.000  -0.2983   0.02655   0.01794  -0.0521   0.9025   0.0643
  -4.750  -0.2717   0.02502   0.01607  -0.0513   0.8965   0.0683
  -4.500  -0.2456   0.02352   0.01462  -0.0510   0.8905   0.0765
  -4.250  -0.2179   0.02228   0.01335  -0.0507   0.8861   0.0914
  -4.000  -0.1999   0.02135   0.01255  -0.0491   0.8791   0.1132
  -3.750  -0.1811   0.02009   0.01167  -0.0473   0.8737   0.1721
  -3.500  -0.1701   0.01877   0.01127  -0.0447   0.8678   0.3219
  -3.250  -0.1591   0.01773   0.01129  -0.0416   0.8619   0.5362
  -3.000  -0.0546   0.01717   0.01156  -0.0521   0.8626   0.8723
  -2.750   0.0149   0.01797   0.01198  -0.0577   0.8602   0.9291
  -2.500   0.0950   0.01826   0.01187  -0.0666   0.8582   0.9649
  -2.250   0.1752   0.01789   0.01118  -0.0771   0.8553   0.9939
  -2.000   0.2098   0.01775   0.01085  -0.0798   0.8492   1.0000
  -1.750   0.2273   0.01785   0.01080  -0.0786   0.8436   1.0000
  -1.500   0.2469   0.01809   0.01094  -0.0784   0.8370   1.0000
  -1.250   0.2659   0.01828   0.01100  -0.0774   0.8312   1.0000
  -1.000   0.2855   0.01855   0.01117  -0.0767   0.8255   1.0000
  -0.750   0.3052   0.01887   0.01141  -0.0760   0.8190   1.0000
  -0.500   0.3251   0.01906   0.01150  -0.0747   0.8142   1.0000
  -0.250   0.3446   0.01955   0.01194  -0.0743   0.8070   1.0000
   0.000   0.3648   0.01980   0.01212  -0.0731   0.8015   1.0000
   0.250   0.3840   0.02026   0.01254  -0.0723   0.7949   1.0000
   0.500   0.4037   0.02062   0.01285  -0.0712   0.7885   1.0000
   0.750   0.4235   0.02099   0.01318  -0.0700   0.7825   1.0000
   1.000   0.4421   0.02148   0.01365  -0.0689   0.7750   1.0000
   1.250   0.4638   0.02166   0.01378  -0.0674   0.7700   1.0000
   1.500   0.4803   0.02236   0.01449  -0.0664   0.7611   1.0000
   1.750   0.5032   0.02245   0.01455  -0.0649   0.7562   1.0000
   2.000   0.5187   0.02320   0.01533  -0.0637   0.7466   1.0000
   2.250   0.5426   0.02321   0.01531  -0.0622   0.7416   1.0000
   2.500   0.5577   0.02396   0.01610  -0.0609   0.7314   1.0000
   2.750   0.5789   0.02418   0.01635  -0.0593   0.7243   1.0000
   3.000   0.5982   0.02452   0.01672  -0.0578   0.7155   1.0000
   3.250   0.6163   0.02497   0.01722  -0.0562   0.7064   1.0000
   3.500   0.6408   0.02484   0.01710  -0.0547   0.6995   1.0000
   3.750   0.6578   0.02535   0.01767  -0.0530   0.6888   1.0000
   4.000   0.6859   0.02485   0.01721  -0.0514   0.6835   1.0000
   4.250   0.7029   0.02527   0.01771  -0.0497   0.6716   1.0000
   4.500   0.7226   0.02543   0.01795  -0.0480   0.6609   1.0000
   4.750   0.7522   0.02467   0.01724  -0.0464   0.6547   1.0000
   5.000   0.7715   0.02476   0.01743  -0.0446   0.6425   1.0000
   5.250   0.7929   0.02464   0.01740  -0.0428   0.6308   1.0000
   5.500   0.8176   0.02415   0.01700  -0.0410   0.6202   1.0000
   5.750   0.8473   0.02314   0.01606  -0.0394   0.6113   1.0000
   6.000   0.8707   0.02264   0.01565  -0.0376   0.5977   1.0000
   6.250   0.8951   0.02201   0.01512  -0.0358   0.5836   1.0000
   6.500   0.9205   0.02124   0.01444  -0.0340   0.5685   1.0000
   6.750   0.9418   0.02078   0.01413  -0.0321   0.5489   1.0000
   7.000   0.9656   0.02007   0.01351  -0.0302   0.5279   1.0000
   7.250   0.9867   0.01961   0.01313  -0.0281   0.5009   1.0000
   7.500   1.0069   0.01928   0.01278  -0.0259   0.4683   1.0000
   7.750   1.0229   0.01939   0.01284  -0.0234   0.4268   1.0000
   8.000   1.0346   0.01993   0.01318  -0.0206   0.3798   1.0000
   8.250   1.0420   0.02087   0.01386  -0.0174   0.3321   1.0000
   8.500   1.0455   0.02206   0.01477  -0.0139   0.2873   1.0000
   8.750   1.0460   0.02339   0.01585  -0.0102   0.2470   1.0000
   9.000   1.0439   0.02482   0.01700  -0.0063   0.2133   1.0000
   9.250   1.0400   0.02628   0.01823  -0.0023   0.1846   1.0000
   9.500   1.0350   0.02770   0.01953   0.0018   0.1605   1.0000
   9.750   1.0314   0.02936   0.02103   0.0052   0.1389   1.0000
  10.000   1.0305   0.03111   0.02265   0.0080   0.1198   1.0000
  10.250   1.0326   0.03309   0.02441   0.0105   0.1029   1.0000
  10.500   1.0377   0.03496   0.02625   0.0126   0.0885   1.0000
  10.750   1.0496   0.03690   0.02808   0.0144   0.0767   1.0000
  11.000   1.0641   0.03869   0.03001   0.0160   0.0689   1.0000
  11.250   1.0822   0.04085   0.03223   0.0171   0.0619   1.0000
  11.500   1.0967   0.04285   0.03437   0.0184   0.0571   1.0000
  11.750   1.1270   0.04638   0.03797   0.0185   0.0528   1.0000
  12.000   1.1275   0.04871   0.04066   0.0206   0.0509   1.0000
  12.250   1.1262   0.05109   0.04332   0.0225   0.0485   1.0000
  12.500   1.1274   0.05391   0.04642   0.0240   0.0471   1.0000
  12.750   1.1256   0.05709   0.04984   0.0254   0.0460   1.0000
  13.000   1.1191   0.06051   0.05351   0.0266   0.0455   1.0000
  13.250   1.1092   0.06418   0.05742   0.0276   0.0450   1.0000
  13.500   1.0944   0.06825   0.06177   0.0281   0.0450   1.0000
  13.750   1.0785   0.07249   0.06623   0.0282   0.0448   1.0000
  14.000   1.0636   0.07692   0.07082   0.0278   0.0442   1.0000
  14.250   1.0140   0.08489   0.07926   0.0249   0.0465   1.0000
  14.500   0.9780   0.09282   0.08744   0.0212   0.0477   1.0000
  14.750   0.9443   0.10151   0.09628   0.0164   0.0490   1.0000
  15.000   0.9094   0.11185   0.10675   0.0102   0.0502   1.0000
  15.250   0.8802   0.12265   0.11760   0.0039   0.0518   1.0000
  15.500   0.8604   0.13245   0.12740  -0.0011   0.0529   1.0000
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