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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 200,000
Max Cl/Cd: 88.43 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e64-il-200000.txt
Download as CSV file: xf-e64-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E64  (8.45%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4007   0.08933   0.08601  -0.0308   1.0000   0.0449
  -7.500  -0.4165   0.08751   0.08428  -0.0294   1.0000   0.0456
  -7.250  -0.4328   0.08552   0.08239  -0.0290   1.0000   0.0461
  -7.000  -0.4416   0.08213   0.07905  -0.0333   1.0000   0.0466
  -6.750  -0.4438   0.07766   0.07456  -0.0388   1.0000   0.0469
  -6.500  -0.4429   0.07333   0.07014  -0.0424   1.0000   0.0470
  -6.250  -0.4484   0.06802   0.06493  -0.0405   1.0000   0.0481
  -6.000  -0.4458   0.06597   0.06292  -0.0380   1.0000   0.0490
  -5.750  -0.4405   0.06354   0.06050  -0.0373   1.0000   0.0500
  -5.500  -0.4217   0.05986   0.05676  -0.0406   0.9982   0.0523
  -5.250  -0.3702   0.04926   0.04543  -0.0585   0.9933   0.0606
  -5.000  -0.3450   0.04595   0.04224  -0.0603   0.9897   0.0625
  -4.750  -0.3105   0.04264   0.03877  -0.0645   0.9862   0.0671
  -4.500  -0.2718   0.03771   0.03338  -0.0706   0.9827   0.0762
  -4.250  -0.2208   0.02682   0.02094  -0.0746   0.9822   0.0343
  -4.000  -0.1844   0.02326   0.01684  -0.0769   0.9796   0.0320
  -3.750  -0.1464   0.02154   0.01470  -0.0788   0.9764   0.0336
  -3.500  -0.1076   0.01967   0.01249  -0.0808   0.9741   0.0332
  -3.250  -0.0677   0.01825   0.01085  -0.0830   0.9722   0.0335
  -3.000  -0.0367   0.01724   0.00975  -0.0836   0.9665   0.0345
  -2.750   0.0013   0.01611   0.00857  -0.0856   0.9629   0.0377
  -2.500   0.0425   0.01536   0.00782  -0.0884   0.9601   0.0521
  -2.250   0.0772   0.01394   0.00723  -0.0905   0.9557   0.2462
  -2.000   0.1115   0.01323   0.00722  -0.0924   0.9505   0.4301
  -1.750   0.1491   0.01269   0.00724  -0.0943   0.9471   0.5935
  -1.500   0.1771   0.01236   0.00722  -0.0940   0.9403   0.7029
  -1.250   0.2064   0.01200   0.00713  -0.0935   0.9349   0.8100
  -1.000   0.2449   0.01160   0.00687  -0.0946   0.9321   0.9539
  -0.750   0.2784   0.01152   0.00664  -0.0959   0.9237   1.0000
  -0.500   0.3214   0.01137   0.00636  -0.0989   0.9200   1.0000
  -0.250   0.3585   0.01126   0.00615  -0.1007   0.9141   1.0000
   0.000   0.3970   0.01110   0.00590  -0.1027   0.9083   1.0000
   0.250   0.4409   0.01085   0.00558  -0.1056   0.9049   1.0000
   0.500   0.4722   0.01075   0.00543  -0.1061   0.8961   1.0000
   0.750   0.5127   0.01049   0.00513  -0.1083   0.8911   1.0000
   1.000   0.5436   0.01037   0.00498  -0.1086   0.8814   1.0000
   1.250   0.5831   0.01010   0.00467  -0.1105   0.8754   1.0000
   1.500   0.6122   0.00999   0.00457  -0.1104   0.8635   1.0000
   1.750   0.6422   0.00989   0.00445  -0.1104   0.8516   1.0000
   2.000   0.6725   0.00979   0.00434  -0.1105   0.8390   1.0000
   2.250   0.7021   0.00972   0.00425  -0.1104   0.8252   1.0000
   2.500   0.7310   0.00967   0.00421  -0.1102   0.8098   1.0000
   2.750   0.7595   0.00966   0.00417  -0.1099   0.7930   1.0000
   3.000   0.7878   0.00967   0.00415  -0.1096   0.7753   1.0000
   3.250   0.8134   0.00975   0.00422  -0.1088   0.7541   1.0000
   3.500   0.8405   0.00983   0.00427  -0.1083   0.7327   1.0000
   3.750   0.8655   0.00996   0.00438  -0.1074   0.7074   1.0000
   4.000   0.8902   0.01013   0.00450  -0.1064   0.6803   1.0000
   4.250   0.9144   0.01034   0.00464  -0.1054   0.6506   1.0000
   4.500   0.9379   0.01061   0.00485  -0.1043   0.6185   1.0000
   4.750   0.9604   0.01092   0.00507  -0.1030   0.5822   1.0000
   5.000   0.9816   0.01131   0.00533  -0.1015   0.5402   1.0000
   5.250   1.0014   0.01180   0.00563  -0.0998   0.4914   1.0000
   5.500   1.0196   0.01240   0.00601  -0.0980   0.4350   1.0000
   5.750   1.0363   0.01315   0.00645  -0.0960   0.3721   1.0000
   6.000   1.0531   0.01397   0.00697  -0.0941   0.3092   1.0000
   6.250   1.0701   0.01484   0.00756  -0.0924   0.2507   1.0000
   6.500   1.0869   0.01581   0.00824  -0.0908   0.1931   1.0000
   6.750   1.1045   0.01677   0.00896  -0.0893   0.1459   1.0000
   7.000   1.1185   0.01818   0.00996  -0.0874   0.0814   1.0000
   7.250   1.1285   0.02015   0.01163  -0.0844   0.0414   1.0000
   7.500   1.1418   0.02161   0.01311  -0.0821   0.0347   1.0000
   7.750   1.1592   0.02262   0.01422  -0.0803   0.0310   1.0000
   8.000   1.1741   0.02387   0.01557  -0.0783   0.0287   1.0000
   8.250   1.1862   0.02563   0.01737  -0.0760   0.0272   1.0000
   8.500   1.2018   0.02781   0.01962  -0.0742   0.0262   1.0000
   8.750   1.2221   0.02948   0.02144  -0.0730   0.0256   1.0000
   9.000   1.2442   0.03152   0.02365  -0.0721   0.0252   1.0000
   9.250   1.2667   0.03394   0.02629  -0.0713   0.0249   1.0000
   9.500   1.2866   0.03650   0.02914  -0.0702   0.0246   1.0000
   9.750   1.3023   0.03887   0.03184  -0.0685   0.0239   1.0000
  10.000   1.3146   0.04136   0.03465  -0.0666   0.0233   1.0000
  10.250   1.3223   0.04472   0.03841  -0.0641   0.0234   1.0000
  10.500   1.3237   0.04845   0.04255  -0.0611   0.0237   1.0000
  10.750   1.3183   0.05219   0.04666  -0.0575   0.0241   1.0000
  11.000   1.3075   0.05588   0.05067  -0.0536   0.0245   1.0000
  11.250   1.2932   0.05970   0.05476  -0.0500   0.0249   1.0000
  11.500   1.2763   0.06381   0.05914  -0.0472   0.0253   1.0000
  11.750   1.2576   0.06842   0.06397  -0.0452   0.0256   1.0000
  12.000   1.1352   0.06867   0.06472  -0.0377   0.0253   1.0000
  12.250   1.1083   0.07488   0.07114  -0.0382   0.0254   1.0000
  12.500   1.0802   0.08145   0.07791  -0.0398   0.0255   1.0000
  12.750   1.0500   0.08840   0.08505  -0.0423   0.0257   1.0000
  13.000   1.0164   0.09520   0.09202  -0.0455   0.0260   1.0000
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