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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 200,000
Max Cl/Cd: 63.38 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e224-il-200000-n5.txt
Download as CSV file: xf-e224-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5426   0.08156   0.07801  -0.0338   1.0000   0.0106
 -10.000  -0.6245   0.05521   0.05146  -0.0528   1.0000   0.0096
  -9.750  -0.6530   0.04901   0.04507  -0.0569   1.0000   0.0094
  -9.500  -0.6755   0.04545   0.04135  -0.0556   1.0000   0.0094
  -9.250  -0.6896   0.04170   0.03730  -0.0539   1.0000   0.0093
  -9.000  -0.6950   0.03854   0.03382  -0.0521   1.0000   0.0094
  -8.750  -0.6959   0.03553   0.03050  -0.0501   1.0000   0.0095
  -8.500  -0.6920   0.03289   0.02754  -0.0480   1.0000   0.0096
  -8.250  -0.6842   0.03063   0.02499  -0.0461   1.0000   0.0097
  -8.000  -0.6740   0.02858   0.02266  -0.0442   1.0000   0.0099
  -7.750  -0.6617   0.02676   0.02058  -0.0424   1.0000   0.0102
  -7.500  -0.6476   0.02513   0.01872  -0.0407   1.0000   0.0105
  -7.250  -0.6323   0.02364   0.01700  -0.0390   1.0000   0.0108
  -7.000  -0.6160   0.02227   0.01544  -0.0373   1.0000   0.0113
  -6.750  -0.5874   0.02093   0.01388  -0.0381   0.9973   0.0121
  -6.500  -0.5544   0.01991   0.01261  -0.0396   0.9939   0.0133
  -6.250  -0.5245   0.01856   0.01119  -0.0408   0.9897   0.0147
  -6.000  -0.4922   0.01755   0.01008  -0.0422   0.9856   0.0161
  -5.750  -0.4591   0.01664   0.00902  -0.0437   0.9819   0.0180
  -5.500  -0.4292   0.01571   0.00799  -0.0445   0.9764   0.0210
  -5.250  -0.3958   0.01498   0.00719  -0.0459   0.9721   0.0285
  -5.000  -0.3631   0.01429   0.00650  -0.0472   0.9677   0.0410
  -4.750  -0.3325   0.01363   0.00596  -0.0482   0.9617   0.0669
  -4.500  -0.2981   0.01303   0.00548  -0.0499   0.9576   0.1022
  -4.250  -0.2668   0.01250   0.00508  -0.0509   0.9517   0.1433
  -4.000  -0.2343   0.01201   0.00474  -0.0522   0.9460   0.1909
  -3.750  -0.2002   0.01153   0.00444  -0.0538   0.9414   0.2462
  -3.500  -0.1710   0.01117   0.00420  -0.0542   0.9333   0.2915
  -3.250  -0.1368   0.01082   0.00395  -0.0556   0.9282   0.3379
  -3.000  -0.1081   0.01053   0.00377  -0.0558   0.9192   0.3820
  -2.750  -0.0753   0.01024   0.00358  -0.0568   0.9127   0.4267
  -2.500  -0.0463   0.00999   0.00344  -0.0570   0.9030   0.4691
  -2.250  -0.0165   0.00977   0.00330  -0.0572   0.8936   0.5097
  -2.000   0.0141   0.00956   0.00317  -0.0576   0.8847   0.5485
  -1.750   0.0422   0.00940   0.00308  -0.0574   0.8735   0.5850
  -1.500   0.0701   0.00925   0.00300  -0.0572   0.8621   0.6198
  -1.250   0.0979   0.00913   0.00293  -0.0569   0.8506   0.6536
  -1.000   0.1252   0.00902   0.00288  -0.0564   0.8386   0.6862
  -0.750   0.1520   0.00894   0.00284  -0.0558   0.8260   0.7176
  -0.500   0.1783   0.00887   0.00280  -0.0551   0.8127   0.7478
  -0.250   0.2042   0.00883   0.00279  -0.0543   0.7989   0.7764
   0.000   0.2297   0.00881   0.00278  -0.0534   0.7844   0.8034
   0.250   0.2550   0.00880   0.00277  -0.0524   0.7696   0.8297
   0.500   0.2802   0.00880   0.00277  -0.0514   0.7542   0.8554
   0.750   0.3061   0.00882   0.00278  -0.0506   0.7382   0.8801
   1.000   0.3333   0.00885   0.00278  -0.0501   0.7216   0.9040
   1.250   0.3630   0.00889   0.00278  -0.0501   0.7043   0.9269
   1.500   0.3962   0.00895   0.00277  -0.0510   0.6860   0.9471
   1.750   0.4315   0.00902   0.00279  -0.0525   0.6662   0.9661
   2.000   0.4677   0.00911   0.00281  -0.0542   0.6453   0.9836
   2.250   0.5037   0.00922   0.00284  -0.0560   0.6233   1.0000
   2.500   0.5262   0.00938   0.00291  -0.0549   0.6024   1.0000
   2.750   0.5493   0.00955   0.00301  -0.0540   0.5808   1.0000
   3.000   0.5727   0.00974   0.00312  -0.0531   0.5583   1.0000
   3.250   0.5965   0.00994   0.00324  -0.0523   0.5348   1.0000
   3.500   0.6203   0.01017   0.00339  -0.0515   0.5107   1.0000
   3.750   0.6440   0.01043   0.00357  -0.0507   0.4855   1.0000
   4.000   0.6677   0.01070   0.00376  -0.0500   0.4588   1.0000
   4.250   0.6914   0.01099   0.00397  -0.0492   0.4313   1.0000
   4.500   0.7150   0.01130   0.00420  -0.0485   0.4037   1.0000
   4.750   0.7384   0.01165   0.00448  -0.0477   0.3744   1.0000
   5.000   0.7614   0.01203   0.00476  -0.0469   0.3442   1.0000
   5.250   0.7845   0.01244   0.00508  -0.0462   0.3130   1.0000
   5.500   0.8071   0.01289   0.00543  -0.0454   0.2807   1.0000
   5.750   0.8297   0.01337   0.00580  -0.0446   0.2501   1.0000
   6.000   0.8524   0.01385   0.00624  -0.0438   0.2231   1.0000
   6.250   0.8746   0.01438   0.00669  -0.0431   0.1949   1.0000
   6.500   0.8956   0.01504   0.00720  -0.0422   0.1610   1.0000
   6.750   0.9163   0.01574   0.00774  -0.0413   0.1278   1.0000
   7.000   0.9371   0.01643   0.00832  -0.0404   0.1022   1.0000
   7.250   0.9580   0.01711   0.00893  -0.0395   0.0836   1.0000
   7.500   0.9789   0.01779   0.00962  -0.0385   0.0686   1.0000
   7.750   0.9993   0.01851   0.01034  -0.0375   0.0557   1.0000
   8.000   1.0187   0.01932   0.01114  -0.0364   0.0444   1.0000
   8.250   1.0368   0.02024   0.01204  -0.0351   0.0356   1.0000
   8.500   1.0559   0.02102   0.01294  -0.0339   0.0310   1.0000
   8.750   1.0726   0.02200   0.01398  -0.0324   0.0276   1.0000
   9.000   1.0878   0.02307   0.01518  -0.0307   0.0252   1.0000
   9.250   1.1044   0.02397   0.01621  -0.0293   0.0229   1.0000
   9.500   1.1196   0.02494   0.01726  -0.0277   0.0209   1.0000
   9.750   1.1303   0.02621   0.01861  -0.0256   0.0194   1.0000
  10.000   1.1392   0.02748   0.01999  -0.0232   0.0181   1.0000
  10.250   1.1507   0.02851   0.02118  -0.0212   0.0166   1.0000
  10.500   1.1600   0.02972   0.02251  -0.0191   0.0155   1.0000
  10.750   1.1673   0.03110   0.02401  -0.0170   0.0147   1.0000
  11.000   1.1725   0.03265   0.02567  -0.0149   0.0139   1.0000
  11.250   1.1719   0.03489   0.02800  -0.0126   0.0131   1.0000
  11.500   1.1773   0.03666   0.02998  -0.0109   0.0126   1.0000
  11.750   1.1821   0.03850   0.03203  -0.0095   0.0119   1.0000
  12.000   1.1856   0.04045   0.03416  -0.0083   0.0110   1.0000
  12.250   1.1871   0.04265   0.03652  -0.0074   0.0104   1.0000
  12.500   1.1869   0.04516   0.03918  -0.0067   0.0101   1.0000
  12.750   1.1852   0.04798   0.04214  -0.0064   0.0098   1.0000
  13.000   1.1815   0.05117   0.04548  -0.0064   0.0095   1.0000
  13.250   1.1754   0.05484   0.04930  -0.0069   0.0092   1.0000
  13.500   1.1682   0.05892   0.05355  -0.0078   0.0091   1.0000
  13.750   1.1563   0.06391   0.05872  -0.0092   0.0089   1.0000
  14.000   1.1455   0.06904   0.06405  -0.0113   0.0088   1.0000
  14.250   1.1339   0.07461   0.06984  -0.0139   0.0087   1.0000
  14.500   1.1210   0.08071   0.07614  -0.0170   0.0087   1.0000
  14.750   1.1061   0.08757   0.08320  -0.0208   0.0087   1.0000
  15.000   1.0911   0.09482   0.09063  -0.0251   0.0087   1.0000
  15.250   1.0744   0.10289   0.09889  -0.0300   0.0087   1.0000
  15.500   1.0574   0.11144   0.10760  -0.0352   0.0087   1.0000
  15.750   1.0385   0.12091   0.11723  -0.0410   0.0087   1.0000
  16.000   1.0192   0.13096   0.12741  -0.0471   0.0088   1.0000
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