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NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 642-015 AIRFOIL (n64015-il)
Reynolds number: 100,000
Max Cl/Cd: 40.33 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64015-il-100000.txt
Download as CSV file: xf-n64015-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015 AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4667   0.12727   0.12255  -0.0018   1.0000   0.1709
 -12.250  -0.4982   0.12219   0.11753  -0.0061   1.0000   0.1775
 -12.000  -0.9138   0.07275   0.06689  -0.0348   1.0000   0.0774
 -11.750  -0.9063   0.06823   0.06226  -0.0348   1.0000   0.0755
 -11.500  -0.9147   0.06393   0.05782  -0.0341   1.0000   0.0743
 -11.250  -0.9272   0.06021   0.05392  -0.0324   1.0000   0.0733
 -11.000  -0.9385   0.05665   0.05011  -0.0302   1.0000   0.0723
 -10.750  -0.9455   0.05299   0.04614  -0.0281   1.0000   0.0713
 -10.500  -0.9480   0.04950   0.04228  -0.0260   1.0000   0.0706
 -10.250  -0.9442   0.04627   0.03869  -0.0242   1.0000   0.0702
 -10.000  -0.9346   0.04357   0.03569  -0.0228   1.0000   0.0710
  -9.750  -0.9223   0.04124   0.03307  -0.0215   1.0000   0.0726
  -9.500  -0.9077   0.03897   0.03046  -0.0202   1.0000   0.0741
  -9.250  -0.8895   0.03677   0.02792  -0.0192   1.0000   0.0753
  -9.000  -0.8699   0.03493   0.02575  -0.0182   1.0000   0.0766
  -8.750  -0.8385   0.03215   0.02308  -0.0191   1.0000   0.0800
  -8.500  -0.8146   0.03071   0.02161  -0.0189   1.0000   0.0843
  -8.250  -0.7905   0.02936   0.02008  -0.0183   1.0000   0.0885
  -8.000  -0.7604   0.02752   0.01843  -0.0188   1.0000   0.0940
  -7.750  -0.7419   0.02652   0.01742  -0.0176   1.0000   0.1010
  -7.500  -0.7275   0.02534   0.01642  -0.0158   1.0000   0.1077
  -7.250  -0.7281   0.02478   0.01590  -0.0116   1.0000   0.1137
  -7.000  -0.7348   0.02421   0.01541  -0.0066   1.0000   0.1197
  -6.750  -0.7408   0.02368   0.01495  -0.0019   1.0000   0.1275
  -6.500  -0.7459   0.02295   0.01433   0.0026   1.0000   0.1379
  -6.250  -0.7336   0.02138   0.01310   0.0034   0.9945   0.1757
  -6.000  -0.7287   0.01808   0.01191   0.0042   0.9816   0.4552
  -5.750  -0.6919   0.01885   0.01271   0.0030   0.9716   0.5527
  -5.500  -0.6538   0.01991   0.01373   0.0022   0.9625   0.5883
  -5.250  -0.6109   0.02098   0.01467   0.0005   0.9553   0.6174
  -5.000  -0.5659   0.02271   0.01643   0.0000   0.9483   0.6388
  -4.750  -0.5114   0.02463   0.01830  -0.0017   0.9443   0.6590
  -4.500  -0.4658   0.02627   0.01988  -0.0019   0.9378   0.6746
  -4.250  -0.4159   0.02748   0.02097  -0.0035   0.9321   0.6881
  -4.000  -0.3828   0.02757   0.02094  -0.0044   0.9237   0.7008
  -3.750  -0.3317   0.02834   0.02161  -0.0066   0.9181   0.7064
  -3.500  -0.3139   0.02776   0.02091  -0.0063   0.9077   0.7173
  -3.250  -0.2706   0.02803   0.02110  -0.0079   0.9009   0.7215
  -3.000  -0.2542   0.02759   0.02057  -0.0070   0.8905   0.7298
  -2.750  -0.2266   0.02728   0.02017  -0.0073   0.8827   0.7356
  -2.500  -0.2009   0.02728   0.02012  -0.0070   0.8739   0.7405
  -2.250  -0.1912   0.02653   0.01928  -0.0055   0.8656   0.7498
  -2.000  -0.1641   0.02667   0.01939  -0.0052   0.8570   0.7535
  -1.750  -0.1367   0.02651   0.01917  -0.0052   0.8505   0.7589
  -1.500  -0.1301   0.02610   0.01871  -0.0032   0.8406   0.7673
  -1.250  -0.0985   0.02610   0.01868  -0.0035   0.8349   0.7712
  -1.000  -0.0809   0.02602   0.01857  -0.0026   0.8276   0.7776
  -0.750  -0.0657   0.02572   0.01825  -0.0015   0.8203   0.7845
  -0.500  -0.0338   0.02569   0.01819  -0.0018   0.8161   0.7885
  -0.250  -0.0236   0.02571   0.01822  -0.0003   0.8068   0.7962
   0.000   0.0001   0.02554   0.01803   0.0000   0.8018   0.8018
   0.250   0.0236   0.02571   0.01822   0.0003   0.7962   0.8068
   0.500   0.0340   0.02569   0.01819   0.0018   0.7885   0.8161
   0.750   0.0658   0.02572   0.01824   0.0015   0.7844   0.8203
   1.000   0.0809   0.02602   0.01857   0.0026   0.7777   0.8276
   1.250   0.0986   0.02610   0.01868   0.0035   0.7712   0.8350
   1.500   0.1301   0.02610   0.01871   0.0032   0.7673   0.8406
   1.750   0.1368   0.02652   0.01918   0.0052   0.7589   0.8505
   2.000   0.1642   0.02667   0.01939   0.0053   0.7535   0.8570
   2.250   0.1915   0.02653   0.01927   0.0055   0.7498   0.8656
   2.500   0.2009   0.02728   0.02012   0.0070   0.7405   0.8739
   2.750   0.2267   0.02728   0.02017   0.0073   0.7356   0.8827
   3.000   0.2538   0.02760   0.02058   0.0071   0.7297   0.8906
   3.250   0.2708   0.02802   0.02109   0.0079   0.7215   0.9009
   3.500   0.3142   0.02775   0.02090   0.0062   0.7173   0.9077
   3.750   0.3318   0.02834   0.02162   0.0066   0.7065   0.9181
   4.000   0.3833   0.02754   0.02091   0.0044   0.7008   0.9236
   4.250   0.4160   0.02748   0.02097   0.0035   0.6881   0.9322
   4.500   0.4657   0.02628   0.01989   0.0019   0.6747   0.9377
   4.750   0.5115   0.02462   0.01830   0.0016   0.6590   0.9443
   5.000   0.5661   0.02269   0.01642   0.0000   0.6388   0.9483
   5.250   0.6109   0.02098   0.01467  -0.0005   0.6174   0.9553
   5.500   0.6538   0.01992   0.01374  -0.0023   0.5884   0.9625
   5.750   0.6920   0.01886   0.01271  -0.0031   0.5527   0.9717
   6.000   0.7287   0.01807   0.01191  -0.0042   0.4546   0.9816
   6.250   0.7338   0.02137   0.01309  -0.0035   0.1758   0.9945
   6.500   0.7459   0.02294   0.01433  -0.0026   0.1380   1.0000
   6.750   0.7407   0.02367   0.01494   0.0019   0.1274   1.0000
   7.000   0.7347   0.02420   0.01540   0.0066   0.1196   1.0000
   7.250   0.7279   0.02477   0.01589   0.0116   0.1136   1.0000
   7.500   0.7274   0.02534   0.01641   0.0158   0.1077   1.0000
   7.750   0.7418   0.02652   0.01742   0.0176   0.1008   1.0000
   8.000   0.7604   0.02753   0.01843   0.0188   0.0939   1.0000
   8.250   0.7904   0.02936   0.02008   0.0184   0.0884   1.0000
   8.500   0.8148   0.03071   0.02161   0.0189   0.0843   1.0000
   8.750   0.8387   0.03216   0.02309   0.0191   0.0800   1.0000
   9.000   0.8701   0.03494   0.02575   0.0182   0.0766   1.0000
   9.250   0.8897   0.03677   0.02792   0.0192   0.0753   1.0000
   9.500   0.9077   0.03897   0.03045   0.0202   0.0740   1.0000
   9.750   0.9224   0.04122   0.03305   0.0215   0.0725   1.0000
  10.000   0.9347   0.04358   0.03569   0.0228   0.0709   1.0000
  10.250   0.9444   0.04628   0.03870   0.0242   0.0702   1.0000
  10.500   0.9483   0.04948   0.04227   0.0260   0.0705   1.0000
  10.750   0.9458   0.05300   0.04615   0.0280   0.0713   1.0000
  11.000   0.9388   0.05667   0.05013   0.0301   0.0723   1.0000
  11.250   0.9267   0.06026   0.05397   0.0324   0.0733   1.0000
  11.500   0.9149   0.06399   0.05789   0.0340   0.0744   1.0000
  11.750   0.9049   0.06825   0.06228   0.0348   0.0754   1.0000
  12.000   0.9141   0.07280   0.06695   0.0347   0.0774   1.0000
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