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NACA 64(2)-215 (naca642215-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(2)-215 (naca642215-il)
Reynolds number: 100,000
Max Cl/Cd: 47.56 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca642215-il-100000.txt
Download as CSV file: xf-naca642215-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(2)-215                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4834   0.10633   0.10115  -0.0261   1.0000   0.1815
 -10.750  -0.7377   0.06404   0.05840  -0.0565   1.0000   0.0840
 -10.500  -0.7530   0.06042   0.05467  -0.0548   1.0000   0.0825
 -10.250  -0.7693   0.05659   0.05062  -0.0529   1.0000   0.0806
 -10.000  -0.7829   0.05296   0.04671  -0.0505   1.0000   0.0793
  -9.750  -0.7959   0.04941   0.04280  -0.0474   1.0000   0.0777
  -9.500  -0.8065   0.04663   0.03966  -0.0435   1.0000   0.0767
  -9.250  -0.8198   0.04446   0.03706  -0.0385   1.0000   0.0757
  -9.000  -0.8241   0.04261   0.03494  -0.0344   1.0000   0.0753
  -8.750  -0.8245   0.04079   0.03287  -0.0308   1.0000   0.0751
  -8.500  -0.8211   0.03884   0.03070  -0.0278   1.0000   0.0753
  -8.250  -0.8145   0.03693   0.02862  -0.0252   1.0000   0.0758
  -8.000  -0.8055   0.03532   0.02690  -0.0231   1.0000   0.0770
  -7.750  -0.7949   0.03407   0.02558  -0.0211   1.0000   0.0792
  -7.500  -0.7827   0.03280   0.02415  -0.0193   0.9998   0.0813
  -7.250  -0.7418   0.03094   0.02196  -0.0222   0.9939   0.0844
  -7.000  -0.7027   0.02904   0.01990  -0.0246   0.9877   0.0879
  -6.750  -0.6614   0.02761   0.01855  -0.0277   0.9822   0.0949
  -6.500  -0.6235   0.02630   0.01716  -0.0298   0.9750   0.1012
  -6.250  -0.5835   0.02507   0.01606  -0.0326   0.9693   0.1125
  -6.000  -0.5522   0.02387   0.01504  -0.0340   0.9609   0.1256
  -5.750  -0.5210   0.02252   0.01395  -0.0357   0.9535   0.1517
  -5.500  -0.5043   0.01986   0.01233  -0.0362   0.9440   0.2701
  -5.250  -0.4898   0.01932   0.01304  -0.0339   0.9336   0.5362
  -5.000  -0.4494   0.02031   0.01395  -0.0350   0.9275   0.5886
  -4.750  -0.4209   0.02127   0.01490  -0.0337   0.9187   0.6146
  -4.500  -0.3818   0.02235   0.01591  -0.0339   0.9129   0.6402
  -4.250  -0.3502   0.02359   0.01714  -0.0323   0.9057   0.6603
  -4.000  -0.3173   0.02479   0.01830  -0.0308   0.8987   0.6791
  -3.750  -0.2752   0.02601   0.01945  -0.0304   0.8947   0.6975
  -3.500  -0.2540   0.02671   0.02010  -0.0278   0.8855   0.7103
  -3.250  -0.2197   0.02685   0.02012  -0.0283   0.8799   0.7230
  -3.000  -0.1951   0.02708   0.02027  -0.0272   0.8717   0.7312
  -2.750  -0.1684   0.02679   0.01987  -0.0274   0.8646   0.7397
  -2.500  -0.1399   0.02680   0.01979  -0.0273   0.8581   0.7456
  -2.250  -0.1252   0.02639   0.01929  -0.0265   0.8492   0.7546
  -2.000  -0.0886   0.02634   0.01917  -0.0274   0.8453   0.7589
  -1.750  -0.0788   0.02634   0.01912  -0.0254   0.8354   0.7663
  -1.500  -0.0499   0.02603   0.01873  -0.0260   0.8302   0.7727
  -1.250  -0.0319   0.02616   0.01884  -0.0246   0.8223   0.7783
  -1.000  -0.0118   0.02588   0.01848  -0.0245   0.8156   0.7868
  -0.750   0.0214   0.02579   0.01835  -0.0250   0.8121   0.7909
  -0.500   0.0295   0.02609   0.01867  -0.0229   0.8030   0.7973
  -0.250   0.0550   0.02589   0.01841  -0.0233   0.7979   0.8046
   0.000   0.0891   0.02577   0.01826  -0.0239   0.7948   0.8092
   0.250   0.0913   0.02623   0.01874  -0.0214   0.7850   0.8172
   0.500   0.1185   0.02620   0.01869  -0.0216   0.7809   0.8232
   0.750   0.1517   0.02612   0.01860  -0.0222   0.7781   0.8292
   1.000   0.1499   0.02678   0.01930  -0.0193   0.7680   0.8385
   1.250   0.1779   0.02682   0.01936  -0.0193   0.7641   0.8448
   1.500   0.2085   0.02675   0.01928  -0.0201   0.7609   0.8529
   1.750   0.2050   0.02763   0.02023  -0.0165   0.7510   0.8620
   2.000   0.2351   0.02757   0.02019  -0.0168   0.7472   0.8706
   2.250   0.2427   0.02822   0.02089  -0.0146   0.7400   0.8810
   2.500   0.2594   0.02858   0.02131  -0.0135   0.7335   0.8905
   2.750   0.2924   0.02848   0.02124  -0.0141   0.7301   0.9003
   3.000   0.2915   0.02950   0.02233  -0.0113   0.7213   0.9140
   3.250   0.3241   0.02965   0.02256  -0.0123   0.7161   0.9240
   3.500   0.3686   0.02941   0.02239  -0.0145   0.7131   0.9331
   3.750   0.3802   0.03062   0.02370  -0.0145   0.7028   0.9483
   4.000   0.4342   0.03034   0.02353  -0.0184   0.6986   0.9555
   4.250   0.4979   0.02951   0.02281  -0.0229   0.6957   0.9601
   4.500   0.5338   0.03018   0.02363  -0.0261   0.6835   0.9713
   4.750   0.6089   0.02824   0.02180  -0.0309   0.6794   0.9722
   5.000   0.6632   0.02732   0.02104  -0.0347   0.6656   0.9782
   5.250   0.7210   0.02526   0.01907  -0.0371   0.6506   0.9838
   5.500   0.7815   0.02285   0.01670  -0.0397   0.6324   0.9887
   5.750   0.8311   0.02116   0.01507  -0.0420   0.6088   0.9972
   6.000   0.8538   0.02029   0.01426  -0.0405   0.5889   1.0000
   6.250   0.8642   0.01970   0.01370  -0.0371   0.5705   1.0000
   6.500   0.8750   0.01904   0.01302  -0.0336   0.5493   1.0000
   6.750   0.8729   0.01886   0.01294  -0.0286   0.5251   1.0000
   7.000   0.8789   0.01848   0.01251  -0.0245   0.4853   1.0000
   7.250   0.8778   0.01867   0.01222  -0.0196   0.3667   1.0000
   7.500   0.8584   0.02092   0.01330  -0.0138   0.2319   1.0000
   7.750   0.8450   0.02316   0.01489  -0.0091   0.1714   1.0000
   8.000   0.8422   0.02500   0.01637  -0.0058   0.1423   1.0000
   8.250   0.8491   0.02655   0.01773  -0.0037   0.1237   1.0000
   8.500   0.8625   0.02800   0.01903  -0.0022   0.1110   1.0000
   8.750   0.8824   0.02945   0.02029  -0.0015   0.1009   1.0000
   9.000   0.9074   0.03078   0.02157  -0.0012   0.0927   1.0000
   9.250   0.9402   0.03244   0.02321  -0.0018   0.0856   1.0000
   9.500   0.9715   0.03405   0.02479  -0.0024   0.0800   1.0000
   9.750   1.0160   0.03676   0.02753  -0.0049   0.0758   1.0000
  10.000   1.0386   0.03857   0.02960  -0.0044   0.0725   1.0000
  10.250   1.0628   0.04055   0.03169  -0.0044   0.0695   1.0000
  10.500   1.0876   0.04305   0.03434  -0.0045   0.0678   1.0000
  10.750   1.1134   0.04664   0.03807  -0.0051   0.0665   1.0000
  11.000   1.1275   0.05038   0.04211  -0.0043   0.0658   1.0000
  11.250   1.1305   0.05297   0.04507  -0.0021   0.0654   1.0000
  11.500   1.1287   0.05565   0.04812   0.0003   0.0650   1.0000
  11.750   1.1210   0.05840   0.05119   0.0031   0.0646   1.0000
  12.000   1.1118   0.06148   0.05455   0.0056   0.0646   1.0000
  12.250   1.0996   0.06487   0.05820   0.0077   0.0647   1.0000
  12.500   1.0880   0.06877   0.06232   0.0091   0.0650   1.0000
  12.750   1.0799   0.07334   0.06708   0.0097   0.0656   1.0000
  13.000   1.0724   0.07754   0.07148   0.0102   0.0663   1.0000
  13.250   1.0069   0.08223   0.07664   0.0100   0.0678   1.0000
  13.500   0.9147   0.09535   0.09024   0.0033   0.0717   1.0000
  13.750   0.8686   0.10689   0.10191  -0.0034   0.0745   1.0000
  14.000   0.8542   0.11479   0.10985  -0.0072   0.0761   1.0000
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