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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.9 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65410-il-1000000-n5.txt
Download as CSV file: xf-naca65410-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7535   0.02223   0.01883  -0.0763   0.9753   0.0045
 -10.000  -0.7284   0.02034   0.01667  -0.0774   0.9690   0.0048
  -9.750  -0.7018   0.01852   0.01457  -0.0786   0.9633   0.0050
  -9.500  -0.6757   0.01727   0.01310  -0.0793   0.9553   0.0051
  -9.250  -0.6495   0.01625   0.01189  -0.0798   0.9471   0.0052
  -9.000  -0.6253   0.01507   0.01051  -0.0799   0.9378   0.0056
  -8.750  -0.6010   0.01431   0.00962  -0.0798   0.9281   0.0058
  -8.500  -0.5755   0.01387   0.00909  -0.0797   0.9196   0.0062
  -8.250  -0.5503   0.01343   0.00854  -0.0795   0.9106   0.0065
  -8.000  -0.5252   0.01296   0.00797  -0.0793   0.9020   0.0069
  -7.750  -0.5000   0.01252   0.00743  -0.0791   0.8939   0.0073
  -7.500  -0.4745   0.01209   0.00690  -0.0790   0.8855   0.0076
  -7.250  -0.4489   0.01170   0.00641  -0.0788   0.8780   0.0080
  -7.000  -0.4232   0.01131   0.00596  -0.0787   0.8700   0.0087
  -6.750  -0.3966   0.01113   0.00574  -0.0787   0.8626   0.0092
  -6.500  -0.3701   0.01089   0.00544  -0.0786   0.8550   0.0099
  -6.250  -0.3437   0.01058   0.00506  -0.0786   0.8482   0.0105
  -6.000  -0.3171   0.01031   0.00472  -0.0785   0.8408   0.0110
  -5.750  -0.2906   0.00999   0.00432  -0.0785   0.8338   0.0115
  -5.500  -0.2642   0.00963   0.00390  -0.0784   0.8264   0.0125
  -5.250  -0.2370   0.00949   0.00374  -0.0785   0.8200   0.0134
  -5.000  -0.2097   0.00930   0.00352  -0.0786   0.8133   0.0143
  -4.750  -0.1826   0.00908   0.00324  -0.0786   0.8070   0.0150
  -4.500  -0.1551   0.00889   0.00299  -0.0787   0.8002   0.0156
  -4.250  -0.1277   0.00877   0.00283  -0.0787   0.7938   0.0160
  -4.000  -0.1005   0.00839   0.00237  -0.0788   0.7872   0.0176
  -3.750  -0.0729   0.00820   0.00215  -0.0789   0.7811   0.0188
  -3.500  -0.0451   0.00805   0.00197  -0.0791   0.7754   0.0200
  -3.250  -0.0172   0.00793   0.00182  -0.0792   0.7691   0.0216
  -3.000   0.0107   0.00782   0.00167  -0.0793   0.7633   0.0227
  -2.750   0.0387   0.00769   0.00149  -0.0795   0.7569   0.0243
  -2.500   0.0665   0.00756   0.00135  -0.0796   0.7512   0.0283
  -2.250   0.0947   0.00746   0.00124  -0.0798   0.7456   0.0317
  -2.000   0.1228   0.00737   0.00114  -0.0799   0.7397   0.0381
  -1.750   0.1508   0.00720   0.00105  -0.0802   0.7342   0.0664
  -1.500   0.1788   0.00685   0.00095  -0.0806   0.7282   0.1578
  -1.250   0.2064   0.00625   0.00083  -0.0811   0.7227   0.3264
  -1.000   0.2340   0.00541   0.00076  -0.0819   0.7172   0.5778
  -0.750   0.2620   0.00528   0.00078  -0.0821   0.7114   0.6366
  -0.500   0.2902   0.00525   0.00080  -0.0822   0.7061   0.6627
  -0.250   0.3184   0.00522   0.00083  -0.0823   0.7002   0.6885
   0.250   0.3752   0.00526   0.00086  -0.0827   0.6893   0.7032
   0.750   0.4317   0.00532   0.00092  -0.0830   0.6783   0.7154
   1.000   0.4596   0.00537   0.00095  -0.0831   0.6668   0.7219
   1.250   0.4870   0.00545   0.00099  -0.0830   0.6493   0.7278
   1.500   0.5146   0.00552   0.00103  -0.0831   0.6357   0.7342
   1.750   0.5421   0.00560   0.00109  -0.0831   0.6200   0.7403
   2.000   0.5687   0.00575   0.00116  -0.0829   0.5918   0.7468
   2.500   0.6109   0.00714   0.00165  -0.0809   0.3685   0.7596
   2.750   0.6316   0.00798   0.00202  -0.0799   0.2531   0.7667
   3.000   0.6523   0.00881   0.00240  -0.0790   0.1420   0.7736
   3.250   0.6749   0.00944   0.00273  -0.0784   0.0675   0.7809
   3.500   0.6998   0.00979   0.00298  -0.0780   0.0386   0.7877
   3.750   0.7260   0.01001   0.00319  -0.0778   0.0313   0.7951
   4.000   0.7519   0.01022   0.00341  -0.0776   0.0268   0.8026
   4.250   0.7781   0.01043   0.00364  -0.0774   0.0237   0.8107
   4.500   0.8041   0.01061   0.00387  -0.0772   0.0219   0.8185
   4.750   0.8297   0.01086   0.00413  -0.0770   0.0192   0.8263
   5.000   0.8547   0.01114   0.00444  -0.0766   0.0163   0.8344
   5.250   0.8801   0.01137   0.00471  -0.0763   0.0154   0.8426
   5.500   0.9051   0.01163   0.00502  -0.0759   0.0143   0.8518
   5.750   0.9295   0.01191   0.00535  -0.0754   0.0134   0.8610
   6.000   0.9535   0.01223   0.00570  -0.0748   0.0126   0.8705
   6.250   0.9765   0.01262   0.00616  -0.0741   0.0118   0.8812
   6.500   0.9979   0.01312   0.00675  -0.0730   0.0112   0.8928
   6.750   1.0204   0.01346   0.00717  -0.0722   0.0111   0.9053
   7.000   1.0420   0.01384   0.00763  -0.0711   0.0109   0.9182
   7.250   1.0629   0.01421   0.00807  -0.0700   0.0106   0.9325
   7.500   1.0827   0.01454   0.00848  -0.0686   0.0102   0.9518
   7.750   1.1057   0.01493   0.00894  -0.0680   0.0099   1.0000
   8.000   1.1281   0.01544   0.00950  -0.0673   0.0095   1.0000
   8.250   1.1504   0.01594   0.01004  -0.0667   0.0092   1.0000
   8.500   1.1727   0.01639   0.01053  -0.0660   0.0088   1.0000
   8.750   1.1942   0.01691   0.01108  -0.0653   0.0085   1.0000
   9.000   1.2137   0.01762   0.01183  -0.0642   0.0080   1.0000
   9.250   1.2288   0.01876   0.01308  -0.0625   0.0076   1.0000
   9.500   1.2487   0.01936   0.01374  -0.0615   0.0075   1.0000
   9.750   1.2688   0.01989   0.01434  -0.0606   0.0074   1.0000
  10.000   1.2872   0.02049   0.01502  -0.0593   0.0072   1.0000
  10.250   1.3045   0.02106   0.01566  -0.0579   0.0070   1.0000
  10.500   1.3214   0.02160   0.01626  -0.0565   0.0067   1.0000
  10.750   1.3371   0.02224   0.01696  -0.0549   0.0064   1.0000
  11.000   1.3525   0.02288   0.01767  -0.0534   0.0062   1.0000
  11.250   1.3673   0.02357   0.01843  -0.0518   0.0060   1.0000
  11.500   1.3825   0.02420   0.01911  -0.0503   0.0057   1.0000
  11.750   1.3964   0.02497   0.01994  -0.0488   0.0056   1.0000
  12.000   1.4097   0.02579   0.02081  -0.0473   0.0053   1.0000
  12.250   1.4188   0.02703   0.02217  -0.0454   0.0051   1.0000
  12.500   1.4288   0.02819   0.02344  -0.0437   0.0050   1.0000
  12.750   1.4391   0.02935   0.02470  -0.0421   0.0049   1.0000
  13.000   1.4483   0.03062   0.02609  -0.0405   0.0048   1.0000
  13.250   1.4572   0.03193   0.02751  -0.0390   0.0046   1.0000
  13.500   1.4660   0.03327   0.02896  -0.0377   0.0044   1.0000
  13.750   1.4729   0.03481   0.03061  -0.0363   0.0043   1.0000
  14.000   1.4813   0.03623   0.03212  -0.0352   0.0041   1.0000
  14.250   1.4876   0.03790   0.03389  -0.0341   0.0040   1.0000
  14.500   1.4954   0.03944   0.03550  -0.0332   0.0038   1.0000
  14.750   1.5004   0.04132   0.03748  -0.0323   0.0037   1.0000
  15.000   1.5051   0.04329   0.03953  -0.0316   0.0035   1.0000
  15.250   1.5074   0.04559   0.04194  -0.0310   0.0034   1.0000
  15.500   1.5062   0.04839   0.04487  -0.0305   0.0033   1.0000
  15.750   1.5023   0.05162   0.04824  -0.0302   0.0032   1.0000
  16.000   1.4944   0.05549   0.05226  -0.0303   0.0031   1.0000
  16.250   1.4878   0.05941   0.05634  -0.0308   0.0031   1.0000
  16.500   1.4776   0.06404   0.06114  -0.0317   0.0031   1.0000
  16.750   1.4657   0.06922   0.06648  -0.0332   0.0030   1.0000
  17.000   1.4515   0.07514   0.07257  -0.0354   0.0030   1.0000
  17.250   1.4333   0.08218   0.07979  -0.0385   0.0030   1.0000
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