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NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-415 AIRFOIL (n63415-il)
Reynolds number: 50,000
Max Cl/Cd: 27.76 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63415-il-50000-n5.txt
Download as CSV file: xf-n63415-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-415 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4864   0.10374   0.09610  -0.0490   1.0000   0.0653
 -12.000  -0.5035   0.09531   0.08770  -0.0538   1.0000   0.0650
 -11.750  -0.5277   0.08661   0.07900  -0.0592   1.0000   0.0645
 -11.500  -0.5563   0.07865   0.07102  -0.0643   1.0000   0.0640
 -11.250  -0.5852   0.07205   0.06435  -0.0682   1.0000   0.0635
 -11.000  -0.6120   0.06686   0.05905  -0.0703   1.0000   0.0632
 -10.750  -0.6369   0.06283   0.05491  -0.0707   1.0000   0.0633
 -10.500  -0.6597   0.05982   0.05179  -0.0692   1.0000   0.0633
 -10.250  -0.6788   0.05715   0.04899  -0.0670   1.0000   0.0636
 -10.000  -0.6949   0.05466   0.04631  -0.0643   1.0000   0.0643
  -9.750  -0.7084   0.05238   0.04380  -0.0613   1.0000   0.0651
  -9.500  -0.7198   0.05026   0.04139  -0.0580   1.0000   0.0659
  -9.250  -0.7245   0.04831   0.03926  -0.0550   1.0000   0.0669
  -9.000  -0.7218   0.04670   0.03763  -0.0525   1.0000   0.0683
  -8.750  -0.7190   0.04511   0.03591  -0.0500   1.0000   0.0695
  -8.500  -0.7149   0.04357   0.03421  -0.0476   1.0000   0.0713
  -8.250  -0.7092   0.04207   0.03251  -0.0454   1.0000   0.0736
  -8.000  -0.6785   0.03985   0.02974  -0.0475   0.9923   0.0775
  -7.750  -0.6463   0.03810   0.02806  -0.0491   0.9857   0.0812
  -7.500  -0.6146   0.03667   0.02643  -0.0506   0.9784   0.0866
  -7.250  -0.5801   0.03526   0.02488  -0.0521   0.9723   0.0920
  -7.000  -0.5506   0.03415   0.02375  -0.0529   0.9644   0.0982
  -6.750  -0.5167   0.03301   0.02250  -0.0546   0.9583   0.1067
  -6.500  -0.4906   0.03199   0.02141  -0.0550   0.9493   0.1159
  -6.250  -0.4596   0.03080   0.02024  -0.0567   0.9428   0.1302
  -6.000  -0.4374   0.02964   0.01914  -0.0570   0.9332   0.1484
  -5.750  -0.4092   0.02802   0.01783  -0.0591   0.9265   0.1846
  -5.500  -0.3918   0.02646   0.01684  -0.0594   0.9167   0.2542
  -5.250  -0.3628   0.02563   0.01686  -0.0603   0.9108   0.3914
  -5.000  -0.3421   0.02586   0.01720  -0.0588   0.9009   0.4641
  -4.750  -0.3090   0.02630   0.01753  -0.0592   0.8950   0.5207
  -4.500  -0.2884   0.02689   0.01804  -0.0571   0.8854   0.5556
  -4.250  -0.2581   0.02761   0.01868  -0.0560   0.8793   0.5859
  -4.000  -0.2372   0.02810   0.01906  -0.0540   0.8704   0.6077
  -3.750  -0.2091   0.02855   0.01937  -0.0529   0.8639   0.6267
  -3.500  -0.1855   0.02881   0.01950  -0.0516   0.8561   0.6432
  -3.250  -0.1604   0.02888   0.01941  -0.0509   0.8485   0.6581
  -3.000  -0.1274   0.02894   0.01931  -0.0512   0.8437   0.6692
  -2.750  -0.1109   0.02899   0.01927  -0.0494   0.8337   0.6796
  -2.500  -0.0794   0.02880   0.01890  -0.0504   0.8281   0.6920
  -2.250  -0.0605   0.02894   0.01897  -0.0486   0.8196   0.6999
  -2.000  -0.0327   0.02880   0.01869  -0.0490   0.8131   0.7108
  -1.750  -0.0065   0.02880   0.01860  -0.0486   0.8067   0.7192
  -1.500   0.0143   0.02880   0.01851  -0.0479   0.7984   0.7289
  -1.250   0.0453   0.02870   0.01830  -0.0483   0.7935   0.7376
  -1.000   0.0622   0.02881   0.01836  -0.0470   0.7845   0.7466
  -0.750   0.0898   0.02876   0.01823  -0.0471   0.7786   0.7554
  -0.500   0.1140   0.02879   0.01820  -0.0467   0.7722   0.7641
  -0.250   0.1345   0.02890   0.01827  -0.0459   0.7642   0.7734
   0.000   0.1648   0.02881   0.01813  -0.0462   0.7595   0.7817
   0.250   0.1803   0.02909   0.01839  -0.0450   0.7506   0.7919
   0.500   0.2063   0.02910   0.01839  -0.0446   0.7449   0.8002
   0.750   0.2314   0.02918   0.01844  -0.0445   0.7389   0.8108
   1.000   0.2480   0.02945   0.01873  -0.0430   0.7307   0.8201
   1.250   0.2778   0.02940   0.01866  -0.0433   0.7262   0.8301
   1.500   0.2917   0.02981   0.01910  -0.0417   0.7173   0.8416
   1.750   0.3163   0.02988   0.01920  -0.0412   0.7116   0.8519
   2.000   0.3453   0.02987   0.01919  -0.0413   0.7071   0.8629
   2.250   0.3561   0.03041   0.01980  -0.0395   0.6975   0.8764
   2.500   0.3862   0.03036   0.01979  -0.0397   0.6930   0.8884
   2.750   0.4003   0.03090   0.02040  -0.0385   0.6841   0.9033
   3.000   0.4297   0.03099   0.02056  -0.0389   0.6783   0.9177
   3.250   0.4695   0.03084   0.02048  -0.0407   0.6747   0.9312
   3.500   0.4887   0.03169   0.02144  -0.0413   0.6640   0.9508
   3.750   0.5357   0.03161   0.02147  -0.0446   0.6596   0.9657
   4.000   0.5609   0.03241   0.02238  -0.0464   0.6495   1.0000
   4.250   0.5901   0.03249   0.02250  -0.0470   0.6439   1.0000
   4.500   0.6030   0.03341   0.02348  -0.0465   0.6341   1.0000
   4.750   0.6345   0.03357   0.02369  -0.0474   0.6279   1.0000
   5.000   0.6521   0.03445   0.02463  -0.0473   0.6184   1.0000
   5.250   0.6836   0.03461   0.02489  -0.0481   0.6117   1.0000
   5.500   0.7014   0.03549   0.02586  -0.0478   0.6016   1.0000
   5.750   0.7352   0.03544   0.02590  -0.0485   0.5948   1.0000
   6.000   0.7506   0.03637   0.02693  -0.0478   0.5833   1.0000
   6.250   0.7921   0.03570   0.02641  -0.0486   0.5771   1.0000
   6.500   0.8056   0.03658   0.02740  -0.0475   0.5640   1.0000
   6.750   0.8273   0.03687   0.02781  -0.0467   0.5522   1.0000
   7.000   0.8740   0.03550   0.02662  -0.0474   0.5438   1.0000
   7.250   0.8909   0.03587   0.02713  -0.0460   0.5293   1.0000
   7.500   0.9106   0.03592   0.02733  -0.0447   0.5144   1.0000
   7.750   0.9336   0.03559   0.02714  -0.0433   0.4983   1.0000
   8.000   0.9595   0.03489   0.02657  -0.0419   0.4801   1.0000
   8.250   0.9707   0.03514   0.02692  -0.0397   0.4587   1.0000
   8.500   0.9821   0.03538   0.02726  -0.0375   0.4339   1.0000
   8.750   0.9907   0.03593   0.02787  -0.0354   0.4049   1.0000
   9.000   1.0014   0.03636   0.02826  -0.0335   0.3697   1.0000
   9.250   1.0092   0.03722   0.02897  -0.0315   0.3283   1.0000
   9.500   1.0144   0.03848   0.02993  -0.0296   0.2840   1.0000
   9.750   1.0139   0.04052   0.03167  -0.0280   0.2440   1.0000
  10.000   1.0108   0.04305   0.03392  -0.0267   0.2110   1.0000
  10.250   1.0077   0.04581   0.03647  -0.0258   0.1835   1.0000
  10.500   1.0058   0.04862   0.03911  -0.0250   0.1619   1.0000
  10.750   1.0053   0.05143   0.04180  -0.0244   0.1441   1.0000
  11.000   1.0066   0.05416   0.04444  -0.0239   0.1300   1.0000
  11.250   1.0100   0.05674   0.04694  -0.0234   0.1189   1.0000
  11.500   1.0147   0.05922   0.04938  -0.0230   0.1095   1.0000
  11.750   1.0233   0.06144   0.05167  -0.0225   0.1009   1.0000
  12.000   1.0328   0.06353   0.05368  -0.0220   0.0948   1.0000
  12.250   1.0448   0.06559   0.05592  -0.0215   0.0883   1.0000
  12.500   1.0578   0.06741   0.05765  -0.0209   0.0832   1.0000
  12.750   1.0724   0.06951   0.06005  -0.0204   0.0785   1.0000
  13.000   1.0853   0.07160   0.06224  -0.0201   0.0743   1.0000
  13.250   1.1014   0.07352   0.06418  -0.0196   0.0707   1.0000
  13.500   1.1081   0.07666   0.06766  -0.0196   0.0678   1.0000
  13.750   1.1137   0.07981   0.07102  -0.0199   0.0652   1.0000
  14.000   1.1205   0.08268   0.07398  -0.0201   0.0629   1.0000
  14.250   1.1273   0.08580   0.07720  -0.0204   0.0610   1.0000
  14.500   1.1165   0.09107   0.08284  -0.0219   0.0600   1.0000
  14.750   1.1032   0.09690   0.08900  -0.0240   0.0592   1.0000
  15.000   1.0863   0.10354   0.09593  -0.0269   0.0586   1.0000
  15.250   1.0648   0.11131   0.10398  -0.0309   0.0584   1.0000
  15.500   1.0373   0.12088   0.11380  -0.0364   0.0585   1.0000
  15.750   1.0025   0.13317   0.12632  -0.0441   0.0591   1.0000
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