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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 200,000
Max Cl/Cd: 81.76 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e64-il-200000-n5.txt
Download as CSV file: xf-e64-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4122   0.08748   0.08414  -0.0344   1.0000   0.0261
  -7.750  -0.4229   0.08517   0.08190  -0.0328   1.0000   0.0262
  -7.500  -0.4349   0.08314   0.07994  -0.0307   1.0000   0.0263
  -7.250  -0.4261   0.07795   0.07478  -0.0366   0.9970   0.0262
  -6.750  -0.3849   0.05932   0.05599  -0.0584   0.9862   0.0137
  -6.500  -0.3629   0.05191   0.04841  -0.0676   0.9802   0.0132
  -6.250  -0.3364   0.04395   0.04014  -0.0763   0.9751   0.0127
  -6.000  -0.3095   0.03641   0.03210  -0.0828   0.9703   0.0122
  -5.750  -0.2820   0.03045   0.02551  -0.0866   0.9652   0.0120
  -5.500  -0.2494   0.02594   0.02030  -0.0897   0.9623   0.0119
  -5.250  -0.2151   0.02285   0.01662  -0.0920   0.9603   0.0121
  -5.000  -0.1876   0.02112   0.01445  -0.0923   0.9553   0.0132
  -4.750  -0.1558   0.01976   0.01268  -0.0933   0.9518   0.0139
  -4.500  -0.1227   0.01808   0.01076  -0.0946   0.9493   0.0142
  -4.250  -0.0886   0.01667   0.00921  -0.0961   0.9473   0.0146
  -4.000  -0.0603   0.01571   0.00817  -0.0964   0.9425   0.0151
  -3.750  -0.0288   0.01493   0.00729  -0.0973   0.9384   0.0158
  -3.500   0.0058   0.01424   0.00649  -0.0988   0.9356   0.0170
  -3.250   0.0420   0.01367   0.00579  -0.1005   0.9334   0.0190
  -3.000   0.0704   0.01320   0.00529  -0.1007   0.9275   0.0239
  -2.750   0.1039   0.01261   0.00472  -0.1018   0.9235   0.0408
  -2.500   0.1391   0.01187   0.00434  -0.1037   0.9205   0.1287
  -2.250   0.1701   0.01126   0.00415  -0.1048   0.9156   0.2403
  -2.000   0.2003   0.01070   0.00402  -0.1056   0.9098   0.3660
  -1.750   0.2345   0.01030   0.00384  -0.1069   0.9058   0.4512
  -1.500   0.2628   0.01003   0.00375  -0.1070   0.8985   0.5231
  -1.250   0.2945   0.00973   0.00364  -0.1076   0.8927   0.5948
  -1.000   0.3226   0.00948   0.00357  -0.1074   0.8852   0.6637
  -0.750   0.3515   0.00925   0.00348  -0.1072   0.8781   0.7288
  -0.500   0.3763   0.00908   0.00344  -0.1060   0.8692   0.7886
  -0.250   0.4033   0.00887   0.00331  -0.1052   0.8617   0.8494
   0.000   0.4283   0.00872   0.00320  -0.1040   0.8511   0.9165
   0.250   0.4659   0.00858   0.00303  -0.1058   0.8412   1.0000
   0.500   0.4967   0.00858   0.00295  -0.1063   0.8305   1.0000
   0.750   0.5271   0.00860   0.00288  -0.1067   0.8190   1.0000
   1.000   0.5559   0.00863   0.00284  -0.1068   0.8057   1.0000
   1.250   0.5846   0.00868   0.00282  -0.1068   0.7913   1.0000
   1.500   0.6129   0.00875   0.00283  -0.1067   0.7755   1.0000
   1.750   0.6405   0.00883   0.00285  -0.1065   0.7585   1.0000
   2.000   0.6678   0.00893   0.00289  -0.1063   0.7403   1.0000
   2.250   0.6950   0.00906   0.00293  -0.1060   0.7207   1.0000
   2.500   0.7214   0.00920   0.00302  -0.1055   0.6989   1.0000
   3.000   0.7730   0.00957   0.00322  -0.1044   0.6503   1.0000
   3.250   0.7980   0.00980   0.00338  -0.1037   0.6234   1.0000
   3.500   0.8225   0.01006   0.00355  -0.1030   0.5943   1.0000
   3.750   0.8463   0.01036   0.00374  -0.1021   0.5625   1.0000
   4.000   0.8694   0.01070   0.00396  -0.1011   0.5280   1.0000
   4.250   0.8919   0.01109   0.00423  -0.1000   0.4907   1.0000
   4.500   0.9141   0.01151   0.00452  -0.0990   0.4532   1.0000
   4.750   0.9358   0.01198   0.00485  -0.0978   0.4150   1.0000
   5.000   0.9563   0.01255   0.00523  -0.0966   0.3670   1.0000
   5.250   0.9748   0.01329   0.00569  -0.0951   0.3070   1.0000
   5.500   0.9935   0.01409   0.00619  -0.0937   0.2487   1.0000
   5.750   1.0135   0.01482   0.00671  -0.0925   0.2036   1.0000
   6.000   1.0323   0.01569   0.00730  -0.0913   0.1527   1.0000
   6.250   1.0521   0.01650   0.00791  -0.0902   0.1145   1.0000
   6.500   1.0716   0.01733   0.00860  -0.0890   0.0816   1.0000
   6.750   1.0909   0.01820   0.00933  -0.0878   0.0530   1.0000
   7.000   1.1092   0.01917   0.01018  -0.0864   0.0306   1.0000
   7.250   1.1281   0.02009   0.01110  -0.0850   0.0218   1.0000
   7.500   1.1470   0.02097   0.01204  -0.0836   0.0188   1.0000
   7.750   1.1662   0.02178   0.01296  -0.0823   0.0168   1.0000
   8.000   1.1838   0.02272   0.01401  -0.0808   0.0153   1.0000
   8.250   1.1998   0.02379   0.01519  -0.0791   0.0144   1.0000
   8.500   1.2155   0.02481   0.01637  -0.0773   0.0139   1.0000
   8.750   1.2296   0.02593   0.01763  -0.0753   0.0134   1.0000
   9.000   1.2417   0.02711   0.01895  -0.0730   0.0131   1.0000
   9.250   1.2528   0.02838   0.02035  -0.0706   0.0127   1.0000
   9.500   1.2633   0.02976   0.02185  -0.0683   0.0124   1.0000
   9.750   1.2735   0.03123   0.02349  -0.0660   0.0122   1.0000
  10.000   1.2834   0.03282   0.02521  -0.0638   0.0120   1.0000
  10.250   1.2932   0.03452   0.02707  -0.0616   0.0117   1.0000
  10.500   1.3025   0.03632   0.02903  -0.0596   0.0115   1.0000
  10.750   1.3107   0.03817   0.03103  -0.0576   0.0113   1.0000
  11.000   1.3171   0.04017   0.03319  -0.0557   0.0109   1.0000
  11.250   1.3215   0.04258   0.03575  -0.0537   0.0106   1.0000
  11.500   1.3225   0.04582   0.03922  -0.0517   0.0103   1.0000
  11.750   1.3231   0.04822   0.04187  -0.0498   0.0101   1.0000
  12.000   1.3214   0.05105   0.04499  -0.0481   0.0100   1.0000
  12.250   1.3170   0.05424   0.04845  -0.0466   0.0100   1.0000
  12.500   1.3101   0.05779   0.05227  -0.0455   0.0099   1.0000
  12.750   1.3006   0.06175   0.05650  -0.0449   0.0099   1.0000
  13.000   1.2892   0.06618   0.06119  -0.0449   0.0099   1.0000
  13.250   1.2757   0.07113   0.06640  -0.0457   0.0098   1.0000
  13.500   1.2606   0.07669   0.07221  -0.0473   0.0098   1.0000
  13.750   1.2443   0.08286   0.07860  -0.0497   0.0098   1.0000
  14.000   1.2268   0.08975   0.08572  -0.0531   0.0098   1.0000
  14.250   1.2089   0.09732   0.09349  -0.0574   0.0099   1.0000
  14.500   1.1903   0.10569   0.10206  -0.0625   0.0099   1.0000
  14.750   1.1713   0.11491   0.11145  -0.0685   0.0100   1.0000
  15.000   1.1520   0.12496   0.12166  -0.0752   0.0100   1.0000
  15.250   1.1322   0.13590   0.13271  -0.0824   0.0101   1.0000
  15.500   1.1120   0.14776   0.14468  -0.0900   0.0102   1.0000
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