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NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(2)-415 (naca652415-il)
Reynolds number: 50,000
Max Cl/Cd: 24.04 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca652415-il-50000-n5.txt
Download as CSV file: xf-naca652415-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5105   0.08500   0.07761  -0.0734   1.0000   0.0574
 -11.000  -0.5307   0.08081   0.07343  -0.0741   1.0000   0.0572
 -10.750  -0.5524   0.07737   0.07001  -0.0735   1.0000   0.0571
 -10.500  -0.5760   0.07472   0.06739  -0.0716   1.0000   0.0569
 -10.250  -0.6022   0.07287   0.06559  -0.0681   1.0000   0.0566
 -10.000  -0.6325   0.07164   0.06440  -0.0632   1.0000   0.0565
  -9.750  -0.6592   0.07020   0.06295  -0.0585   1.0000   0.0563
  -9.500  -0.6843   0.06845   0.06112  -0.0541   1.0000   0.0563
  -9.250  -0.7009   0.06594   0.05845  -0.0513   0.9983   0.0562
  -9.000  -0.6997   0.06153   0.05351  -0.0531   0.9885   0.0569
  -8.750  -0.6914   0.05771   0.04925  -0.0543   0.9802   0.0579
  -8.500  -0.6717   0.05459   0.04594  -0.0559   0.9740   0.0591
  -8.250  -0.6564   0.05166   0.04268  -0.0564   0.9664   0.0599
  -8.000  -0.6346   0.04866   0.03926  -0.0576   0.9607   0.0606
  -7.750  -0.6168   0.04628   0.03655  -0.0575   0.9533   0.0616
  -7.500  -0.5905   0.04403   0.03390  -0.0587   0.9480   0.0641
  -7.250  -0.5692   0.04214   0.03159  -0.0586   0.9413   0.0663
  -7.000  -0.5415   0.04027   0.02929  -0.0590   0.9358   0.0681
  -6.750  -0.5070   0.03840   0.02726  -0.0605   0.9322   0.0699
  -6.500  -0.4815   0.03718   0.02598  -0.0603   0.9265   0.0725
  -6.250  -0.4521   0.03616   0.02483  -0.0606   0.9212   0.0770
  -6.000  -0.4162   0.03521   0.02366  -0.0615   0.9176   0.0816
  -5.750  -0.3861   0.03424   0.02271  -0.0619   0.9135   0.0859
  -5.500  -0.3680   0.03359   0.02198  -0.0605   0.9064   0.0918
  -5.250  -0.3424   0.03270   0.02107  -0.0608   0.9016   0.0999
  -5.000  -0.3237   0.03196   0.02022  -0.0599   0.8955   0.1096
  -4.750  -0.3091   0.03110   0.01943  -0.0586   0.8887   0.1239
  -4.500  -0.2882   0.02962   0.01832  -0.0590   0.8841   0.1639
  -4.250  -0.2880   0.02782   0.01748  -0.0563   0.8761   0.2901
  -4.000  -0.2784   0.02782   0.01886  -0.0511   0.8707   0.5635
  -3.750  -0.2540   0.02878   0.01969  -0.0487   0.8669   0.6439
  -3.500  -0.2532   0.03016   0.02111  -0.0413   0.8586   0.6918
  -3.250  -0.2369   0.03226   0.02320  -0.0340   0.8542   0.7469
  -3.000  -0.2038   0.03315   0.02386  -0.0323   0.8515   0.7715
  -2.750  -0.2000   0.03311   0.02369  -0.0288   0.8438   0.7833
  -2.500  -0.1738   0.03314   0.02352  -0.0286   0.8392   0.7913
  -2.250  -0.1463   0.03295   0.02310  -0.0292   0.8356   0.8001
  -2.000  -0.1332   0.03300   0.02302  -0.0271   0.8294   0.8072
  -1.750  -0.1186   0.03288   0.02275  -0.0258   0.8237   0.8157
  -1.500  -0.0872   0.03284   0.02255  -0.0268   0.8202   0.8211
  -1.250  -0.0706   0.03281   0.02239  -0.0258   0.8151   0.8288
  -1.000  -0.0569   0.03288   0.02236  -0.0241   0.8090   0.8354
  -0.750  -0.0316   0.03287   0.02223  -0.0244   0.8051   0.8419
  -0.500  -0.0014   0.03281   0.02205  -0.0255   0.8021   0.8484
  -0.250   0.0029   0.03306   0.02226  -0.0224   0.7947   0.8559
   0.000   0.0236   0.03311   0.02223  -0.0221   0.7901   0.8634
   0.250   0.0548   0.03319   0.02223  -0.0232   0.7871   0.8690
   0.500   0.0647   0.03343   0.02242  -0.0213   0.7810   0.8778
   0.750   0.0852   0.03366   0.02263  -0.0209   0.7759   0.8847
   1.000   0.1122   0.03378   0.02270  -0.0214   0.7722   0.8923
   1.250   0.1463   0.03389   0.02278  -0.0231   0.7695   0.8986
   1.500   0.1488   0.03439   0.02329  -0.0203   0.7616   0.9097
   1.750   0.1787   0.03465   0.02355  -0.0216   0.7576   0.9170
   2.000   0.2116   0.03482   0.02371  -0.0231   0.7545   0.9253
   2.250   0.2285   0.03539   0.02432  -0.0229   0.7479   0.9357
   2.500   0.2588   0.03580   0.02477  -0.0246   0.7430   0.9446
   2.750   0.2971   0.03609   0.02510  -0.0273   0.7395   0.9530
   3.000   0.3271   0.03667   0.02575  -0.0293   0.7340   0.9633
   3.250   0.3590   0.03729   0.02646  -0.0318   0.7279   0.9737
   3.500   0.4020   0.03763   0.02690  -0.0355   0.7239   0.9830
   3.750   0.4234   0.03825   0.02760  -0.0364   0.7169   1.0000
   4.000   0.4316   0.03860   0.02797  -0.0344   0.7098   1.0000
   4.250   0.4625   0.03876   0.02818  -0.0354   0.7060   1.0000
   4.750   0.4977   0.03992   0.02947  -0.0347   0.6910   1.0000
   5.000   0.5080   0.04088   0.03048  -0.0337   0.6811   1.0000
   5.250   0.5410   0.04114   0.03087  -0.0349   0.6757   1.0000
   5.500   0.5548   0.04206   0.03188  -0.0343   0.6656   1.0000
   5.750   0.5889   0.04222   0.03218  -0.0354   0.6597   1.0000
   6.000   0.6030   0.04312   0.03319  -0.0347   0.6486   1.0000
   6.250   0.6420   0.04291   0.03318  -0.0358   0.6428   1.0000
   6.500   0.6558   0.04374   0.03414  -0.0349   0.6301   1.0000
   6.750   0.6762   0.04421   0.03477  -0.0343   0.6183   1.0000
   7.000   0.7189   0.04331   0.03414  -0.0351   0.6111   1.0000
   7.500   0.7630   0.04308   0.03432  -0.0329   0.5815   1.0000
   7.750   0.7925   0.04146   0.03294  -0.0311   0.5614   1.0000
   8.000   0.8131   0.03958   0.03123  -0.0279   0.5293   1.0000
   8.250   0.8244   0.03879   0.03055  -0.0248   0.4880   1.0000
   8.500   0.8340   0.03885   0.03067  -0.0224   0.4358   1.0000
   8.750   0.8696   0.03618   0.02707  -0.0186   0.2962   1.0000
   9.000   0.8622   0.03870   0.02886  -0.0160   0.2148   1.0000
   9.250   0.8546   0.04164   0.03129  -0.0141   0.1632   1.0000
   9.500   0.8517   0.04440   0.03371  -0.0127   0.1307   1.0000
   9.750   0.8539   0.04683   0.03596  -0.0116   0.1116   1.0000
  10.000   0.8594   0.04902   0.03806  -0.0106   0.0992   1.0000
  10.250   0.8672   0.05105   0.04003  -0.0097   0.0900   1.0000
  10.500   0.8786   0.05281   0.04180  -0.0088   0.0823   1.0000
  10.750   0.8947   0.05426   0.04331  -0.0079   0.0766   1.0000
  11.000   0.9137   0.05556   0.04468  -0.0071   0.0710   1.0000
  11.250   0.9398   0.05656   0.04572  -0.0064   0.0662   1.0000
  11.500   0.9768   0.05729   0.04669  -0.0058   0.0620   1.0000
  11.750   1.0062   0.05862   0.04804  -0.0055   0.0584   1.0000
  12.000   1.0343   0.06052   0.05017  -0.0053   0.0556   1.0000
  12.250   1.0546   0.06300   0.05300  -0.0050   0.0537   1.0000
  12.500   1.0698   0.06586   0.05618  -0.0046   0.0525   1.0000
  12.750   1.0779   0.06896   0.05957  -0.0042   0.0514   1.0000
  13.000   1.0817   0.07220   0.06306  -0.0038   0.0505   1.0000
  13.250   1.0822   0.07558   0.06665  -0.0035   0.0495   1.0000
  13.500   1.0818   0.07907   0.07032  -0.0034   0.0487   1.0000
  14.000   1.0662   0.08753   0.07921  -0.0040   0.0476   1.0000
  14.250   1.0482   0.09271   0.08469  -0.0050   0.0475   1.0000
  14.500   1.0281   0.09843   0.09068  -0.0067   0.0475   1.0000
  14.750   1.0072   0.10465   0.09712  -0.0091   0.0476   1.0000
  15.000   0.9855   0.11150   0.10417  -0.0123   0.0477   1.0000
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