Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E224 (10.17%) (e224-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.89 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e224-il-1000000-n5.txt
Download as CSV file: xf-e224-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E224  (10.17%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7474   0.08300   0.08113  -0.0307   1.0000   0.0029
 -13.000  -0.7868   0.07088   0.06892  -0.0373   1.0000   0.0028
 -12.750  -0.8526   0.05220   0.04998  -0.0504   1.0000   0.0027
 -12.500  -0.8754   0.04311   0.04069  -0.0587   1.0000   0.0026
 -12.250  -0.8883   0.03782   0.03524  -0.0631   1.0000   0.0027
 -12.000  -0.8972   0.03468   0.03197  -0.0641   1.0000   0.0027
 -11.750  -0.9195   0.03194   0.02905  -0.0612   1.0000   0.0027
 -11.500  -0.9215   0.03011   0.02707  -0.0589   1.0000   0.0028
 -11.250  -0.9212   0.02817   0.02496  -0.0567   1.0000   0.0028
 -11.000  -0.9190   0.02622   0.02281  -0.0543   1.0000   0.0028
 -10.750  -0.9099   0.02489   0.02133  -0.0524   1.0000   0.0028
 -10.500  -0.9004   0.02352   0.01980  -0.0503   1.0000   0.0029
 -10.250  -0.8843   0.02218   0.01830  -0.0494   0.9995   0.0029
 -10.000  -0.8580   0.02078   0.01671  -0.0505   0.9977   0.0030
  -9.750  -0.8311   0.01941   0.01515  -0.0516   0.9957   0.0030
  -9.500  -0.8024   0.01834   0.01394  -0.0527   0.9941   0.0031
  -9.250  -0.7757   0.01751   0.01300  -0.0532   0.9916   0.0032
  -9.000  -0.7482   0.01648   0.01184  -0.0539   0.9890   0.0032
  -8.750  -0.7185   0.01578   0.01104  -0.0549   0.9867   0.0033
  -8.500  -0.6885   0.01488   0.01002  -0.0560   0.9847   0.0033
  -8.250  -0.6584   0.01369   0.00865  -0.0572   0.9830   0.0035
  -8.000  -0.6327   0.01304   0.00794  -0.0572   0.9783   0.0038
  -7.750  -0.6036   0.01249   0.00733  -0.0578   0.9745   0.0041
  -7.500  -0.5729   0.01198   0.00675  -0.0586   0.9713   0.0043
  -7.250  -0.5441   0.01150   0.00621  -0.0591   0.9667   0.0046
  -7.000  -0.5154   0.01104   0.00569  -0.0594   0.9609   0.0048
  -6.750  -0.4843   0.01063   0.00520  -0.0603   0.9560   0.0051
  -6.500  -0.4562   0.01026   0.00478  -0.0604   0.9477   0.0053
  -6.250  -0.4269   0.00994   0.00439  -0.0608   0.9396   0.0056
  -6.000  -0.3991   0.00956   0.00393  -0.0608   0.9297   0.0062
  -5.750  -0.3719   0.00926   0.00359  -0.0607   0.9193   0.0072
  -5.500  -0.3448   0.00901   0.00328  -0.0606   0.9088   0.0083
  -5.250  -0.3181   0.00876   0.00300  -0.0603   0.8977   0.0118
  -5.000  -0.2915   0.00853   0.00275  -0.0601   0.8860   0.0170
  -4.750  -0.2649   0.00832   0.00252  -0.0598   0.8739   0.0230
  -4.500  -0.2382   0.00812   0.00231  -0.0596   0.8615   0.0316
  -4.250  -0.2117   0.00791   0.00210  -0.0594   0.8485   0.0450
  -4.000  -0.1851   0.00771   0.00192  -0.0591   0.8352   0.0628
  -3.750  -0.1588   0.00745   0.00173  -0.0589   0.8220   0.0915
  -3.500  -0.1322   0.00724   0.00158  -0.0587   0.8089   0.1204
  -3.250  -0.1053   0.00709   0.00144  -0.0585   0.7955   0.1435
  -3.000  -0.0787   0.00688   0.00132  -0.0583   0.7821   0.1806
  -2.750  -0.0520   0.00669   0.00121  -0.0582   0.7684   0.2196
  -2.500  -0.0249   0.00658   0.00112  -0.0580   0.7538   0.2449
  -2.250   0.0022   0.00649   0.00104  -0.0579   0.7391   0.2693
  -2.000   0.0292   0.00639   0.00097  -0.0577   0.7240   0.3002
  -1.750   0.0563   0.00630   0.00092  -0.0576   0.7086   0.3308
  -1.500   0.0835   0.00622   0.00087  -0.0575   0.6931   0.3610
  -1.250   0.1106   0.00616   0.00083  -0.0573   0.6773   0.3913
  -1.000   0.1378   0.00611   0.00081  -0.0572   0.6608   0.4195
  -0.750   0.1649   0.00608   0.00080  -0.0571   0.6441   0.4478
  -0.500   0.1921   0.00606   0.00079  -0.0569   0.6267   0.4756
  -0.250   0.2193   0.00605   0.00079  -0.0568   0.6088   0.5030
   0.000   0.2465   0.00604   0.00080  -0.0567   0.5911   0.5301
   0.250   0.2736   0.00606   0.00082  -0.0565   0.5727   0.5572
   0.500   0.3007   0.00607   0.00085  -0.0564   0.5547   0.5851
   0.750   0.3278   0.00608   0.00089  -0.0562   0.5352   0.6142
   1.250   0.3816   0.00618   0.00099  -0.0558   0.4948   0.6679
   1.500   0.4084   0.00624   0.00105  -0.0556   0.4746   0.6926
   1.750   0.4352   0.00631   0.00113  -0.0554   0.4539   0.7164
   2.000   0.4618   0.00641   0.00121  -0.0551   0.4316   0.7412
   2.250   0.4882   0.00650   0.00131  -0.0549   0.4103   0.7660
   2.500   0.5143   0.00662   0.00141  -0.0545   0.3868   0.7904
   2.750   0.5403   0.00674   0.00153  -0.0541   0.3630   0.8141
   3.000   0.5661   0.00687   0.00165  -0.0537   0.3426   0.8369
   3.250   0.5914   0.00702   0.00178  -0.0532   0.3188   0.8594
   3.500   0.6163   0.00717   0.00192  -0.0525   0.2965   0.8818
   3.750   0.6403   0.00737   0.00208  -0.0517   0.2700   0.9039
   4.000   0.6635   0.00762   0.00224  -0.0507   0.2385   0.9272
   4.250   0.6881   0.00781   0.00240  -0.0500   0.2180   0.9523
   4.500   0.7188   0.00812   0.00259  -0.0508   0.1877   0.9779
   4.750   0.7502   0.00844   0.00281  -0.0518   0.1616   1.0000
   5.000   0.7753   0.00875   0.00303  -0.0515   0.1392   1.0000
   5.250   0.8001   0.00911   0.00327  -0.0510   0.1155   1.0000
   5.500   0.8250   0.00945   0.00352  -0.0506   0.0971   1.0000
   5.750   0.8500   0.00979   0.00378  -0.0502   0.0813   1.0000
   6.000   0.8749   0.01013   0.00406  -0.0497   0.0666   1.0000
   6.250   0.8997   0.01048   0.00435  -0.0493   0.0540   1.0000
   6.500   0.9245   0.01082   0.00465  -0.0489   0.0443   1.0000
   6.750   0.9490   0.01118   0.00497  -0.0484   0.0355   1.0000
   7.000   0.9733   0.01157   0.00532  -0.0479   0.0271   1.0000
   7.250   0.9974   0.01197   0.00570  -0.0474   0.0208   1.0000
   7.500   1.0217   0.01234   0.00607  -0.0468   0.0170   1.0000
   7.750   1.0453   0.01276   0.00648  -0.0462   0.0142   1.0000
   8.000   1.0694   0.01313   0.00687  -0.0457   0.0126   1.0000
   8.250   1.0935   0.01348   0.00726  -0.0452   0.0118   1.0000
   8.500   1.1170   0.01388   0.00767  -0.0446   0.0108   1.0000
   8.750   1.1399   0.01432   0.00815  -0.0439   0.0099   1.0000
   9.000   1.1621   0.01483   0.00870  -0.0431   0.0089   1.0000
   9.250   1.1852   0.01521   0.00912  -0.0424   0.0086   1.0000
   9.500   1.2079   0.01562   0.00958  -0.0417   0.0081   1.0000
   9.750   1.2301   0.01604   0.01004  -0.0410   0.0074   1.0000
  10.000   1.2515   0.01653   0.01056  -0.0402   0.0066   1.0000
  10.250   1.2717   0.01710   0.01117  -0.0391   0.0057   1.0000
  10.500   1.2927   0.01757   0.01168  -0.0382   0.0052   1.0000
  10.750   1.3125   0.01811   0.01226  -0.0372   0.0046   1.0000
  11.000   1.3313   0.01870   0.01288  -0.0360   0.0040   1.0000
  11.250   1.3485   0.01938   0.01361  -0.0346   0.0036   1.0000
  11.500   1.3655   0.02003   0.01433  -0.0331   0.0034   1.0000
  11.750   1.3804   0.02068   0.01505  -0.0313   0.0032   1.0000
  12.000   1.3929   0.02136   0.01580  -0.0292   0.0030   1.0000
  12.250   1.4039   0.02211   0.01662  -0.0268   0.0028   1.0000
  12.500   1.4141   0.02293   0.01752  -0.0245   0.0026   1.0000
  12.750   1.4234   0.02381   0.01847  -0.0223   0.0025   1.0000
  13.000   1.4310   0.02484   0.01958  -0.0200   0.0024   1.0000
  13.250   1.4367   0.02604   0.02087  -0.0177   0.0022   1.0000
  13.500   1.4417   0.02734   0.02228  -0.0156   0.0021   1.0000
  13.750   1.4436   0.02894   0.02399  -0.0134   0.0020   1.0000
  14.000   1.4457   0.03063   0.02580  -0.0116   0.0020   1.0000
  14.250   1.4494   0.03229   0.02755  -0.0102   0.0020   1.0000
  14.500   1.4500   0.03433   0.02971  -0.0090   0.0020   1.0000
  14.750   1.4541   0.03617   0.03165  -0.0082   0.0019   1.0000
  15.000   1.4503   0.03892   0.03453  -0.0075   0.0019   1.0000
  15.250   1.4494   0.04154   0.03727  -0.0073   0.0019   1.0000
  15.500   1.4483   0.04438   0.04021  -0.0073   0.0018   1.0000
  15.750   1.4391   0.04838   0.04436  -0.0080   0.0018   1.0000
  16.000   1.4322   0.05236   0.04849  -0.0090   0.0018   1.0000
  16.250   1.4242   0.05674   0.05300  -0.0105   0.0018   1.0000
  16.500   1.4151   0.06155   0.05794  -0.0125   0.0017   1.0000
  16.750   1.4002   0.06758   0.06412  -0.0153   0.0017   1.0000
  17.000   1.3830   0.07436   0.07105  -0.0187   0.0017   1.0000
  17.250   1.3670   0.08127   0.07810  -0.0223   0.0017   1.0000
  17.500   1.3464   0.08933   0.08631  -0.0268   0.0017   1.0000
  17.750   1.3168   0.09960   0.09676  -0.0326   0.0017   1.0000
  18.000   1.2926   0.10908   0.10639  -0.0380   0.0017   1.0000
  18.250   1.2611   0.12052   0.11797  -0.0446   0.0018   1.0000
  18.500   1.2332   0.13145   0.12904  -0.0510   0.0018   1.0000
<< Back to E224 (10.17%) (e224-il)

Polar data table (+)

Polar graphs


<< Back to E224 (10.17%) (e224-il)