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NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(2)-415 (naca652415-il)
Reynolds number: 200,000
Max Cl/Cd: 70.81 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca652415-il-200000.txt
Download as CSV file: xf-naca652415-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4881   0.08509   0.08159  -0.0726   1.0000   0.0726
 -10.750  -0.5231   0.08247   0.07904  -0.0705   1.0000   0.0726
 -10.500  -0.5499   0.08157   0.07822  -0.0653   1.0000   0.0724
 -10.250  -0.5821   0.07572   0.07212  -0.0739   0.9887   0.0727
 -10.000  -0.5975   0.07221   0.06819  -0.0789   0.9759   0.0732
  -9.750  -0.5610   0.06378   0.06015  -0.0808   0.9784   0.0761
  -9.500  -0.5425   0.06022   0.05652  -0.0840   0.9731   0.0788
  -9.250  -0.5387   0.05628   0.05231  -0.0872   0.9640   0.0828
  -9.000  -0.4536   0.03772   0.03384  -0.0950   0.9499   0.0936
  -8.500  -0.5226   0.03638   0.02985  -0.0891   0.9413   0.0508
  -8.250  -0.5038   0.03275   0.02605  -0.0886   0.9335   0.0495
  -8.000  -0.4770   0.03009   0.02307  -0.0893   0.9286   0.0494
  -7.750  -0.4506   0.02868   0.02132  -0.0895   0.9233   0.0502
  -7.500  -0.4285   0.02703   0.01940  -0.0887   0.9157   0.0508
  -7.250  -0.3979   0.02468   0.01688  -0.0894   0.9117   0.0514
  -7.000  -0.3708   0.02310   0.01525  -0.0895   0.9063   0.0524
  -6.750  -0.3460   0.02207   0.01420  -0.0891   0.8997   0.0540
  -6.500  -0.3181   0.02121   0.01329  -0.0892   0.8951   0.0564
  -6.250  -0.2953   0.02050   0.01252  -0.0883   0.8881   0.0584
  -6.000  -0.2708   0.01977   0.01172  -0.0877   0.8821   0.0600
  -5.750  -0.2460   0.01887   0.01078  -0.0872   0.8779   0.0621
  -5.500  -0.2294   0.01818   0.01016  -0.0856   0.8702   0.0656
  -5.250  -0.2071   0.01764   0.00959  -0.0848   0.8647   0.0702
  -5.000  -0.1863   0.01700   0.00891  -0.0839   0.8596   0.0753
  -4.750  -0.1675   0.01648   0.00840  -0.0827   0.8525   0.0836
  -4.500  -0.1465   0.01568   0.00770  -0.0819   0.8478   0.1078
  -4.250  -0.1455   0.01308   0.00699  -0.0794   0.8413   0.4793
  -4.000  -0.1232   0.01317   0.00736  -0.0780   0.8357   0.5981
  -3.750  -0.0960   0.01338   0.00751  -0.0773   0.8318   0.6335
  -3.500  -0.0697   0.01367   0.00777  -0.0765   0.8276   0.6546
  -3.250  -0.0457   0.01399   0.00808  -0.0755   0.8218   0.6713
  -3.000  -0.0205   0.01446   0.00854  -0.0742   0.8177   0.6938
  -2.750   0.0026   0.01531   0.00947  -0.0712   0.8146   0.7189
  -2.500   0.0239   0.01587   0.01005  -0.0690   0.8093   0.7338
  -2.250   0.0488   0.01601   0.01015  -0.0683   0.8043   0.7409
  -2.000   0.0772   0.01590   0.00993  -0.0687   0.8008   0.7475
  -1.750   0.1054   0.01590   0.00987  -0.0685   0.7980   0.7512
  -1.500   0.1289   0.01600   0.00995  -0.0681   0.7926   0.7558
  -1.250   0.1567   0.01592   0.00978  -0.0687   0.7880   0.7617
  -1.000   0.1847   0.01585   0.00966  -0.0687   0.7846   0.7650
  -0.750   0.2135   0.01582   0.00959  -0.0688   0.7820   0.7685
  -0.500   0.2369   0.01597   0.00974  -0.0685   0.7769   0.7732
  -0.250   0.2649   0.01594   0.00966  -0.0692   0.7725   0.7786
   0.000   0.2921   0.01591   0.00963  -0.0690   0.7692   0.7817
   0.250   0.3210   0.01590   0.00959  -0.0692   0.7666   0.7854
   0.500   0.3451   0.01607   0.00978  -0.0691   0.7620   0.7901
   0.750   0.3717   0.01614   0.00985  -0.0694   0.7574   0.7954
   1.000   0.3982   0.01616   0.00989  -0.0691   0.7540   0.7988
   1.250   0.4271   0.01616   0.00988  -0.0694   0.7514   0.8030
   1.500   0.4533   0.01632   0.01006  -0.0696   0.7476   0.8081
   1.750   0.4765   0.01650   0.01030  -0.0692   0.7424   0.8129
   2.000   0.5023   0.01658   0.01042  -0.0689   0.7389   0.8171
   2.250   0.5318   0.01658   0.01044  -0.0693   0.7362   0.8222
   2.500   0.5606   0.01667   0.01055  -0.0699   0.7329   0.8275
   2.750   0.5789   0.01699   0.01098  -0.0685   0.7271   0.8320
   3.000   0.6057   0.01704   0.01108  -0.0684   0.7231   0.8376
   3.250   0.6375   0.01695   0.01101  -0.0692   0.7201   0.8434
   3.500   0.6579   0.01714   0.01131  -0.0679   0.7145   0.8483
   3.750   0.6824   0.01722   0.01146  -0.0675   0.7089   0.8544
   4.000   0.7133   0.01706   0.01134  -0.0679   0.7050   0.8601
   4.250   0.7359   0.01710   0.01148  -0.0668   0.6993   0.8660
   4.500   0.7626   0.01697   0.01141  -0.0665   0.6919   0.8734
   4.750   0.7926   0.01650   0.01098  -0.0662   0.6853   0.8785
   5.000   0.8233   0.01563   0.01008  -0.0655   0.6715   0.8848
   5.250   0.8450   0.01493   0.00939  -0.0635   0.6527   0.8923
   5.500   0.8665   0.01448   0.00899  -0.0616   0.6371   0.9005
   5.750   0.8886   0.01418   0.00873  -0.0601   0.6239   0.9088
   6.000   0.9079   0.01396   0.00858  -0.0582   0.6082   0.9189
   6.250   0.9220   0.01375   0.00847  -0.0553   0.5895   0.9298
   6.500   0.9364   0.01353   0.00830  -0.0524   0.5648   0.9429
   6.750   0.9496   0.01341   0.00818  -0.0495   0.5264   0.9592
   7.000   0.9596   0.01400   0.00823  -0.0468   0.4117   0.9807
   7.250   0.9453   0.01572   0.00920  -0.0415   0.2948   1.0000
   7.500   0.9290   0.01808   0.01083  -0.0368   0.1821   1.0000
   7.750   0.9173   0.02059   0.01268  -0.0331   0.0983   1.0000
   8.000   0.9200   0.02235   0.01426  -0.0310   0.0746   1.0000
   8.250   0.9281   0.02379   0.01567  -0.0294   0.0651   1.0000
   8.500   0.9328   0.02548   0.01730  -0.0276   0.0598   1.0000
   8.750   0.9451   0.02670   0.01858  -0.0264   0.0555   1.0000
   9.000   0.9555   0.02806   0.01993  -0.0252   0.0521   1.0000
   9.250   0.9639   0.02971   0.02153  -0.0237   0.0492   1.0000
   9.500   0.9793   0.03085   0.02276  -0.0228   0.0469   1.0000
   9.750   0.9955   0.03203   0.02396  -0.0219   0.0451   1.0000
  10.000   1.0135   0.03321   0.02512  -0.0211   0.0434   1.0000
  10.250   1.0415   0.03452   0.02633  -0.0210   0.0415   1.0000
  10.500   1.0685   0.03575   0.02767  -0.0208   0.0400   1.0000
  10.750   1.0927   0.03695   0.02900  -0.0206   0.0387   1.0000
  11.000   1.1194   0.03834   0.03051  -0.0206   0.0375   1.0000
  11.250   1.1482   0.03998   0.03227  -0.0208   0.0366   1.0000
  11.500   1.1764   0.04186   0.03430  -0.0211   0.0359   1.0000
  11.750   1.2026   0.04412   0.03674  -0.0212   0.0355   1.0000
  12.000   1.2233   0.04663   0.03948  -0.0209   0.0353   1.0000
  12.250   1.2393   0.04920   0.04221  -0.0204   0.0348   1.0000
  12.500   1.2537   0.05231   0.04552  -0.0200   0.0343   1.0000
  12.750   1.2610   0.05590   0.04935  -0.0189   0.0340   1.0000
  13.000   1.2573   0.05866   0.05238  -0.0168   0.0342   1.0000
  13.250   1.2409   0.06165   0.05576  -0.0139   0.0348   1.0000
  13.500   1.1861   0.06866   0.06353  -0.0101   0.0369   1.0000
  13.750   1.1632   0.07416   0.06934  -0.0091   0.0380   1.0000
  14.000   1.1431   0.07958   0.07500  -0.0089   0.0390   1.0000
  14.250   1.1248   0.08516   0.08076  -0.0093   0.0397   1.0000
  14.500   0.9564   0.08962   0.08587  -0.0069   0.0388   1.0000
  14.750   0.9181   0.09562   0.09210  -0.0093   0.0394   1.0000
  15.000   0.8845   0.10238   0.09904  -0.0128   0.0399   1.0000
  15.250   0.8898   0.10594   0.10262  -0.0134   0.0414   1.0000
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