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NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63(2)-615 (naca632615-il)
Reynolds number: 50,000
Max Cl/Cd: 24.85 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca632615-il-50000-n5.txt
Download as CSV file: xf-naca632615-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-615                                  
  
 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  -0.3813   0.10310   0.09570  -0.0584   1.0000   0.0667
 -11.000  -0.3908   0.09805   0.09074  -0.0603   1.0000   0.0670
 -10.750  -0.4043   0.09229   0.08508  -0.0625   1.0000   0.0668
 -10.500  -0.4263   0.08537   0.07826  -0.0656   1.0000   0.0663
 -10.000  -0.5695   0.07011   0.06303  -0.0697   1.0000   0.0603
  -9.750  -0.6001   0.06834   0.06129  -0.0664   1.0000   0.0602
  -9.500  -0.6258   0.06617   0.05907  -0.0635   1.0000   0.0601
  -9.250  -0.6480   0.06371   0.05651  -0.0610   1.0000   0.0601
  -9.000  -0.6419   0.05923   0.05171  -0.0646   0.9917   0.0613
  -8.750  -0.6198   0.05651   0.04889  -0.0674   0.9845   0.0634
  -8.500  -0.6043   0.05286   0.04486  -0.0702   0.9756   0.0653
  -8.250  -0.5872   0.04918   0.04069  -0.0726   0.9672   0.0669
  -8.000  -0.5636   0.04570   0.03657  -0.0755   0.9603   0.0696
  -7.750  -0.5419   0.04328   0.03383  -0.0765   0.9522   0.0723
  -7.500  -0.5111   0.04124   0.03160  -0.0785   0.9466   0.0753
  -7.250  -0.4871   0.03948   0.02955  -0.0790   0.9388   0.0792
  -7.000  -0.4559   0.03766   0.02737  -0.0805   0.9329   0.0835
  -6.750  -0.4274   0.03634   0.02603  -0.0811   0.9267   0.0876
  -6.500  -0.3998   0.03521   0.02467  -0.0814   0.9196   0.0935
  -6.250  -0.3660   0.03401   0.02344  -0.0826   0.9149   0.0994
  -6.000  -0.3429   0.03319   0.02252  -0.0821   0.9069   0.1062
  -5.750  -0.3136   0.03222   0.02154  -0.0828   0.9009   0.1153
  -5.500  -0.2821   0.03123   0.02049  -0.0840   0.8956   0.1272
  -5.250  -0.2617   0.03038   0.01967  -0.0836   0.8869   0.1424
  -5.000  -0.2292   0.02907   0.01853  -0.0858   0.8819   0.1733
  -4.750  -0.2084   0.02771   0.01766  -0.0864   0.8739   0.2328
  -4.500  -0.1833   0.02670   0.01762  -0.0869   0.8675   0.3805
  -4.250  -0.1528   0.02693   0.01801  -0.0866   0.8623   0.4795
  -4.000  -0.1348   0.02742   0.01848  -0.0844   0.8533   0.5275
  -3.750  -0.1047   0.02798   0.01891  -0.0837   0.8480   0.5734
  -3.500  -0.0896   0.02870   0.01961  -0.0803   0.8394   0.6007
  -3.250  -0.0655   0.02918   0.01997  -0.0785   0.8331   0.6277
  -3.000  -0.0398   0.02955   0.02022  -0.0768   0.8280   0.6482
  -2.750  -0.0245   0.02986   0.02044  -0.0744   0.8189   0.6647
  -2.250   0.0234   0.03006   0.02034  -0.0727   0.8061   0.6921
  -2.000   0.0477   0.03009   0.02026  -0.0720   0.7997   0.7030
  -1.750   0.0817   0.02994   0.01993  -0.0731   0.7956   0.7151
  -1.500   0.0943   0.03021   0.02014  -0.0709   0.7862   0.7246
  -1.250   0.1237   0.03014   0.01995  -0.0712   0.7810   0.7348
  -1.000   0.1507   0.03016   0.01985  -0.0714   0.7753   0.7455
  -0.750   0.1677   0.03037   0.02001  -0.0699   0.7672   0.7542
  -0.500   0.2009   0.03027   0.01979  -0.0711   0.7629   0.7648
  -0.250   0.2159   0.03056   0.02006  -0.0693   0.7548   0.7736
   0.000   0.2420   0.03064   0.02006  -0.0694   0.7487   0.7836
   0.250   0.2734   0.03054   0.01990  -0.0698   0.7449   0.7933
   0.500   0.2845   0.03104   0.02039  -0.0680   0.7356   0.8033
   0.750   0.3137   0.03107   0.02036  -0.0685   0.7305   0.8142
   1.000   0.3447   0.03093   0.02019  -0.0686   0.7272   0.8239
   1.250   0.3512   0.03164   0.02093  -0.0663   0.7168   0.8354
   1.500   0.3815   0.03162   0.02088  -0.0668   0.7126   0.8472
   1.750   0.3931   0.03213   0.02143  -0.0648   0.7044   0.8596
   2.000   0.4146   0.03233   0.02165  -0.0640   0.6984   0.8724
   2.250   0.4455   0.03221   0.02154  -0.0643   0.6947   0.8858
   2.500   0.4502   0.03303   0.02243  -0.0619   0.6848   0.9031
   2.750   0.4801   0.03306   0.02248  -0.0623   0.6801   0.9202
   3.250   0.5338   0.03401   0.02358  -0.0644   0.6660   0.9696
   3.500   0.5747   0.03398   0.02357  -0.0670   0.6620   1.0000
   3.750   0.5878   0.03527   0.02488  -0.0672   0.6520   1.0000
   4.000   0.6231   0.03554   0.02517  -0.0690   0.6471   1.0000
   4.250   0.6658   0.03543   0.02510  -0.0714   0.6439   1.0000
   4.500   0.6717   0.03718   0.02688  -0.0707   0.6321   1.0000
   4.750   0.7115   0.03710   0.02687  -0.0725   0.6284   1.0000
   5.000   0.7189   0.03887   0.02868  -0.0719   0.6170   1.0000
   5.250   0.7563   0.03881   0.02871  -0.0731   0.6127   1.0000
   5.500   0.7649   0.04056   0.03051  -0.0725   0.6016   1.0000
   5.750   0.8005   0.04047   0.03051  -0.0734   0.5967   1.0000
   6.250   0.8453   0.04194   0.03218  -0.0733   0.5802   1.0000
   6.750   0.8928   0.04297   0.03343  -0.0729   0.5633   1.0000
   7.000   0.9001   0.04465   0.03523  -0.0718   0.5506   1.0000
   7.250   0.9452   0.04331   0.03405  -0.0722   0.5459   1.0000
   7.500   0.9508   0.04497   0.03582  -0.0709   0.5322   1.0000
   8.000   1.0108   0.04413   0.03532  -0.0699   0.5134   1.0000
   8.250   1.0203   0.04526   0.03659  -0.0685   0.4992   1.0000
   8.500   1.0350   0.04587   0.03735  -0.0672   0.4850   1.0000
   8.750   1.0545   0.04592   0.03758  -0.0659   0.4707   1.0000
   9.000   1.0752   0.04571   0.03752  -0.0645   0.4550   1.0000
   9.250   1.0941   0.04557   0.03753  -0.0630   0.4373   1.0000
   9.500   1.1163   0.04492   0.03701  -0.0614   0.4171   1.0000
   9.750   1.1199   0.04631   0.03850  -0.0598   0.3932   1.0000
  10.000   1.1328   0.04666   0.03888  -0.0581   0.3648   1.0000
  10.250   1.1415   0.04757   0.03974  -0.0565   0.3322   1.0000
  10.500   1.1483   0.04879   0.04083  -0.0550   0.2962   1.0000
  10.750   1.1509   0.05064   0.04242  -0.0535   0.2602   1.0000
  11.000   1.1489   0.05324   0.04479  -0.0524   0.2286   1.0000
  11.250   1.1450   0.05628   0.04765  -0.0516   0.2011   1.0000
  11.500   1.1408   0.05952   0.05072  -0.0510   0.1781   1.0000
  11.750   1.1373   0.06287   0.05396  -0.0506   0.1584   1.0000
  12.000   1.1349   0.06621   0.05720  -0.0504   0.1424   1.0000
  12.250   1.1344   0.06947   0.06039  -0.0502   0.1289   1.0000
  12.500   1.1354   0.07261   0.06350  -0.0501   0.1177   1.0000
  12.750   1.1379   0.07559   0.06639  -0.0499   0.1090   1.0000
  13.000   1.1434   0.07836   0.06925  -0.0498   0.1005   1.0000
  13.250   1.1498   0.08101   0.07192  -0.0496   0.0938   1.0000
  13.500   1.1577   0.08354   0.07454  -0.0494   0.0878   1.0000
  13.750   1.1673   0.08588   0.07690  -0.0492   0.0828   1.0000
  14.000   1.1754   0.08861   0.07985  -0.0492   0.0779   1.0000
  14.250   1.1870   0.09064   0.08184  -0.0489   0.0739   1.0000
  14.500   1.1944   0.09372   0.08519  -0.0490   0.0705   1.0000
  14.750   1.1987   0.09714   0.08885  -0.0496   0.0673   1.0000
  15.000   1.2063   0.09989   0.09166  -0.0499   0.0645   1.0000
  15.250   1.2126   0.10309   0.09499  -0.0504   0.0622   1.0000
  15.500   1.2052   0.10855   0.10083  -0.0524   0.0607   1.0000
  15.750   1.1959   0.11439   0.10697  -0.0548   0.0593   1.0000
  16.000   1.1847   0.12073   0.11357  -0.0578   0.0582   1.0000
  16.250   1.1710   0.12776   0.12084  -0.0615   0.0573   1.0000
  16.500   1.1524   0.13627   0.12959  -0.0665   0.0568   1.0000
  16.750   1.1157   0.14995   0.14356  -0.0753   0.0574   1.0000
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