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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 500,000
Max Cl/Cd: 103.33 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e64-il-500000-n5.txt
Download as CSV file: xf-e64-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4026   0.10334   0.10100  -0.0316   1.0000   0.0098
  -9.500  -0.3996   0.10132   0.09900  -0.0311   1.0000   0.0101
  -9.250  -0.4010   0.09791   0.09561  -0.0315   1.0000   0.0101
  -9.000  -0.3973   0.09636   0.09408  -0.0308   1.0000   0.0106
  -8.500  -0.4016   0.09092   0.08870  -0.0303   1.0000   0.0110
  -8.000  -0.2834   0.05955   0.05744  -0.0518   0.9882   0.0089
  -6.500  -0.2727   0.02391   0.01995  -0.1027   0.9612   0.0061
  -6.250  -0.2460   0.02090   0.01647  -0.1043   0.9576   0.0061
  -6.000  -0.2197   0.01846   0.01361  -0.1051   0.9531   0.0062
  -5.750  -0.1898   0.01587   0.01060  -0.1065   0.9504   0.0064
  -5.500  -0.1581   0.01449   0.00903  -0.1078   0.9483   0.0067
  -5.250  -0.1258   0.01352   0.00792  -0.1090   0.9463   0.0070
  -5.000  -0.0998   0.01278   0.00706  -0.1088   0.9405   0.0074
  -4.750  -0.0689   0.01202   0.00619  -0.1096   0.9367   0.0077
  -4.500  -0.0360   0.01139   0.00547  -0.1108   0.9339   0.0083
  -4.250  -0.0070   0.01095   0.00497  -0.1111   0.9286   0.0090
  -4.000   0.0234   0.01046   0.00439  -0.1117   0.9235   0.0093
  -3.750   0.0559   0.00991   0.00377  -0.1127   0.9194   0.0095
  -3.500   0.0845   0.00938   0.00314  -0.1129   0.9127   0.0102
  -3.250   0.1153   0.00903   0.00271  -0.1135   0.9069   0.0111
  -3.000   0.1448   0.00877   0.00238  -0.1138   0.9000   0.0124
  -2.750   0.1746   0.00856   0.00211  -0.1141   0.8925   0.0144
  -2.500   0.2032   0.00814   0.00185  -0.1144   0.8841   0.0562
  -2.250   0.2324   0.00780   0.00167  -0.1148   0.8759   0.1142
  -2.000   0.2602   0.00757   0.00155  -0.1149   0.8662   0.1597
  -1.750   0.2883   0.00726   0.00146  -0.1151   0.8568   0.2390
  -1.500   0.3162   0.00688   0.00140  -0.1154   0.8469   0.3511
  -1.250   0.3438   0.00670   0.00135  -0.1153   0.8356   0.4157
  -1.000   0.3713   0.00659   0.00131  -0.1153   0.8236   0.4642
  -0.750   0.3987   0.00648   0.00129  -0.1151   0.8112   0.5144
  -0.500   0.4258   0.00638   0.00129  -0.1149   0.7982   0.5690
  -0.250   0.4526   0.00630   0.00130  -0.1146   0.7845   0.6200
   0.000   0.4791   0.00626   0.00132  -0.1143   0.7697   0.6672
   0.250   0.5050   0.00622   0.00135  -0.1137   0.7530   0.7143
   0.500   0.5302   0.00621   0.00139  -0.1130   0.7353   0.7614
   0.750   0.5545   0.00621   0.00145  -0.1121   0.7175   0.8072
   1.000   0.5777   0.00621   0.00150  -0.1108   0.6988   0.8517
   1.250   0.5991   0.00624   0.00154  -0.1091   0.6786   0.8976
   1.500   0.6228   0.00627   0.00156  -0.1080   0.6567   0.9550
   1.750   0.6523   0.00642   0.00159  -0.1083   0.6320   1.0000
   2.000   0.6779   0.00661   0.00167  -0.1079   0.6065   1.0000
   2.250   0.7033   0.00682   0.00178  -0.1074   0.5803   1.0000
   2.500   0.7285   0.00705   0.00189  -0.1068   0.5530   1.0000
   2.750   0.7534   0.00731   0.00202  -0.1063   0.5232   1.0000
   3.000   0.7780   0.00760   0.00217  -0.1057   0.4911   1.0000
   3.250   0.8023   0.00792   0.00236  -0.1051   0.4567   1.0000
   3.500   0.8265   0.00826   0.00255  -0.1044   0.4210   1.0000
   3.750   0.8511   0.00858   0.00275  -0.1039   0.3901   1.0000
   4.000   0.8740   0.00906   0.00301  -0.1031   0.3423   1.0000
   4.250   0.8949   0.00975   0.00336  -0.1020   0.2735   1.0000
   4.500   0.9161   0.01045   0.00372  -0.1011   0.2093   1.0000
   4.750   0.9383   0.01105   0.00408  -0.1002   0.1624   1.0000
   5.000   0.9618   0.01152   0.00442  -0.0996   0.1340   1.0000
   5.250   0.9845   0.01207   0.00481  -0.0989   0.1006   1.0000
   5.500   1.0075   0.01259   0.00521  -0.0981   0.0754   1.0000
   5.750   1.0300   0.01315   0.00564  -0.0973   0.0512   1.0000
   6.000   1.0513   0.01384   0.00618  -0.0964   0.0261   1.0000
   6.250   1.0730   0.01449   0.00675  -0.0954   0.0129   1.0000
   6.500   1.0959   0.01499   0.00728  -0.0946   0.0107   1.0000
   6.750   1.1191   0.01545   0.00781  -0.0938   0.0100   1.0000
   7.000   1.1420   0.01592   0.00835  -0.0930   0.0096   1.0000
   7.250   1.1643   0.01644   0.00894  -0.0921   0.0092   1.0000
   7.500   1.1860   0.01701   0.00958  -0.0911   0.0088   1.0000
   7.750   1.2071   0.01763   0.01030  -0.0901   0.0085   1.0000
   8.000   1.2274   0.01831   0.01105  -0.0889   0.0082   1.0000
   8.250   1.2467   0.01905   0.01188  -0.0876   0.0079   1.0000
   8.500   1.2647   0.01989   0.01280  -0.0861   0.0076   1.0000
   8.750   1.2813   0.02082   0.01382  -0.0844   0.0074   1.0000
   9.000   1.2951   0.02197   0.01506  -0.0823   0.0071   1.0000
   9.250   1.3050   0.02341   0.01663  -0.0796   0.0068   1.0000
   9.500   1.3193   0.02428   0.01760  -0.0776   0.0067   1.0000
   9.750   1.3317   0.02527   0.01870  -0.0753   0.0066   1.0000
  10.000   1.3433   0.02633   0.01987  -0.0730   0.0065   1.0000
  10.250   1.3536   0.02751   0.02117  -0.0706   0.0064   1.0000
  10.500   1.3634   0.02875   0.02253  -0.0682   0.0063   1.0000
  10.750   1.3722   0.03010   0.02402  -0.0659   0.0062   1.0000
  11.000   1.3798   0.03159   0.02565  -0.0635   0.0061   1.0000
  11.250   1.3865   0.03317   0.02739  -0.0612   0.0060   1.0000
  11.500   1.3918   0.03491   0.02930  -0.0589   0.0059   1.0000
  11.750   1.3959   0.03681   0.03136  -0.0567   0.0058   1.0000
  12.000   1.3986   0.03886   0.03358  -0.0547   0.0057   1.0000
  12.250   1.3994   0.04116   0.03607  -0.0527   0.0056   1.0000
  12.500   1.3988   0.04367   0.03876  -0.0510   0.0056   1.0000
  12.750   1.3965   0.04644   0.04171  -0.0495   0.0055   1.0000
  13.000   1.3923   0.04955   0.04501  -0.0484   0.0054   1.0000
  13.250   1.3867   0.05295   0.04860  -0.0476   0.0054   1.0000
  13.500   1.3790   0.05679   0.05264  -0.0474   0.0053   1.0000
  13.750   1.3698   0.06109   0.05713  -0.0477   0.0053   1.0000
  14.000   1.3586   0.06595   0.06218  -0.0486   0.0052   1.0000
  14.250   1.3458   0.07139   0.06782  -0.0502   0.0052   1.0000
  14.500   1.3319   0.07742   0.07404  -0.0526   0.0052   1.0000
  14.750   1.3164   0.08419   0.08100  -0.0558   0.0052   1.0000
  15.000   1.2999   0.09170   0.08870  -0.0598   0.0052   1.0000
  15.250   1.2819   0.10008   0.09726  -0.0647   0.0052   1.0000
  15.500   1.2624   0.10934   0.10671  -0.0703   0.0052   1.0000
  15.750   1.2411   0.11965   0.11720  -0.0767   0.0053   1.0000
  16.000   1.2185   0.13097   0.12869  -0.0839   0.0053   1.0000
  16.250   1.1933   0.14374   0.14163  -0.0919   0.0054   1.0000
  16.500   1.1631   0.15906   0.15711  -0.1014   0.0055   1.0000
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