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NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 642-015A AIRFOIL (n64015a-il)
Reynolds number: 200,000
Max Cl/Cd: 49.92 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64015a-il-200000.txt
Download as CSV file: xf-n64015a-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015A AIRFOIL                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8384   0.08370   0.07950  -0.0373   1.0000   0.0452
 -13.250  -0.8593   0.07763   0.07333  -0.0394   1.0000   0.0445
 -13.000  -0.8833   0.07183   0.06738  -0.0411   1.0000   0.0438
 -12.750  -0.9096   0.06630   0.06164  -0.0419   1.0000   0.0429
 -12.500  -1.0038   0.05676   0.05120  -0.0386   1.0000   0.0394
 -12.250  -1.0205   0.05441   0.04855  -0.0354   1.0000   0.0390
 -12.000  -1.0290   0.05232   0.04622  -0.0321   1.0000   0.0388
 -11.750  -1.0299   0.04975   0.04339  -0.0297   1.0000   0.0387
 -11.500  -1.0272   0.04641   0.03979  -0.0277   1.0000   0.0386
 -11.250  -1.0232   0.04367   0.03677  -0.0255   1.0000   0.0386
 -11.000  -1.0162   0.04102   0.03384  -0.0235   1.0000   0.0387
 -10.750  -1.0008   0.03759   0.03017  -0.0228   1.0000   0.0391
 -10.500  -0.9804   0.03515   0.02765  -0.0225   1.0000   0.0400
 -10.250  -0.9627   0.03369   0.02612  -0.0217   1.0000   0.0411
 -10.000  -0.9438   0.03229   0.02464  -0.0208   1.0000   0.0423
  -9.750  -0.9239   0.03079   0.02299  -0.0199   1.0000   0.0434
  -9.500  -0.9024   0.02930   0.02134  -0.0192   1.0000   0.0445
  -9.250  -0.8812   0.02805   0.01992  -0.0183   1.0000   0.0456
  -9.000  -0.8559   0.02639   0.01819  -0.0181   1.0000   0.0471
  -8.750  -0.8351   0.02515   0.01704  -0.0174   1.0000   0.0492
  -8.500  -0.8184   0.02433   0.01622  -0.0159   1.0000   0.0516
  -8.250  -0.8025   0.02356   0.01538  -0.0141   1.0000   0.0541
  -8.000  -0.7899   0.02243   0.01427  -0.0118   1.0000   0.0566
  -7.750  -0.7829   0.02163   0.01354  -0.0086   1.0000   0.0592
  -7.500  -0.7787   0.02108   0.01300  -0.0048   1.0000   0.0622
  -7.250  -0.7777   0.02076   0.01262  -0.0003   1.0000   0.0652
  -7.000  -0.7855   0.02010   0.01203   0.0052   1.0000   0.0683
  -6.750  -0.7513   0.01911   0.01104   0.0028   0.9945   0.0783
  -6.500  -0.7182   0.01788   0.00993   0.0005   0.9870   0.0946
  -6.250  -0.6863   0.01656   0.00886  -0.0017   0.9796   0.1321
  -6.000  -0.6631   0.01438   0.00759  -0.0030   0.9710   0.2740
  -5.750  -0.6440   0.01290   0.00709  -0.0027   0.9603   0.4593
  -5.500  -0.6085   0.01271   0.00703  -0.0043   0.9541   0.5252
  -5.250  -0.5774   0.01267   0.00699  -0.0049   0.9446   0.5582
  -5.000  -0.5434   0.01267   0.00695  -0.0060   0.9377   0.5833
  -4.750  -0.5138   0.01271   0.00697  -0.0060   0.9281   0.6024
  -4.500  -0.4837   0.01276   0.00697  -0.0062   0.9197   0.6189
  -4.250  -0.4551   0.01279   0.00694  -0.0060   0.9105   0.6328
  -4.000  -0.4286   0.01284   0.00692  -0.0054   0.9008   0.6460
  -3.750  -0.4013   0.01296   0.00701  -0.0048   0.8925   0.6613
  -3.500  -0.3762   0.01315   0.00719  -0.0038   0.8824   0.6757
  -3.250  -0.3475   0.01323   0.00727  -0.0034   0.8749   0.6854
  -3.000  -0.3229   0.01322   0.00718  -0.0026   0.8644   0.6948
  -2.750  -0.2947   0.01323   0.00716  -0.0023   0.8572   0.7020
  -2.500  -0.2700   0.01317   0.00702  -0.0018   0.8473   0.7101
  -2.250  -0.2417   0.01313   0.00695  -0.0016   0.8401   0.7154
  -2.000  -0.2159   0.01308   0.00684  -0.0013   0.8306   0.7221
  -1.750  -0.1888   0.01300   0.00668  -0.0011   0.8235   0.7280
  -1.500  -0.1619   0.01297   0.00666  -0.0009   0.8146   0.7334
  -1.250  -0.1350   0.01291   0.00650  -0.0007   0.8083   0.7406
  -1.000  -0.1083   0.01288   0.00650  -0.0006   0.7996   0.7459
  -0.750  -0.0806   0.01285   0.00642  -0.0004   0.7930   0.7518
  -0.500  -0.0548   0.01282   0.00636  -0.0002   0.7850   0.7592
  -0.250  -0.0268   0.01281   0.00637  -0.0001   0.7784   0.7647
   0.000   0.0000   0.01282   0.00636   0.0000   0.7721   0.7721
   0.250   0.0268   0.01281   0.00637   0.0001   0.7647   0.7784
   0.500   0.0548   0.01282   0.00636   0.0002   0.7592   0.7850
   0.750   0.0806   0.01285   0.00642   0.0004   0.7518   0.7930
   1.000   0.1083   0.01288   0.00650   0.0006   0.7459   0.7996
   1.250   0.1350   0.01291   0.00650   0.0007   0.7406   0.8083
   1.500   0.1619   0.01297   0.00666   0.0009   0.7334   0.8146
   1.750   0.1888   0.01300   0.00668   0.0011   0.7280   0.8235
   2.000   0.2159   0.01308   0.00684   0.0013   0.7221   0.8306
   2.250   0.2417   0.01313   0.00695   0.0016   0.7154   0.8401
   2.500   0.2700   0.01317   0.00702   0.0018   0.7101   0.8473
   2.750   0.2947   0.01323   0.00716   0.0023   0.7020   0.8572
   3.000   0.3229   0.01322   0.00718   0.0026   0.6948   0.8644
   3.250   0.3475   0.01323   0.00727   0.0034   0.6854   0.8749
   3.500   0.3762   0.01315   0.00719   0.0038   0.6758   0.8824
   3.750   0.4014   0.01296   0.00701   0.0048   0.6613   0.8925
   4.000   0.4287   0.01284   0.00692   0.0054   0.6460   0.9008
   4.250   0.4551   0.01279   0.00694   0.0060   0.6328   0.9105
   4.500   0.4837   0.01276   0.00697   0.0062   0.6189   0.9197
   4.750   0.5138   0.01271   0.00697   0.0060   0.6023   0.9281
   5.000   0.5433   0.01267   0.00695   0.0060   0.5833   0.9377
   5.250   0.5775   0.01267   0.00699   0.0049   0.5582   0.9446
   5.500   0.6084   0.01270   0.00703   0.0043   0.5252   0.9542
   5.750   0.6440   0.01290   0.00709   0.0027   0.4595   0.9603
   6.000   0.6632   0.01438   0.00759   0.0030   0.2741   0.9711
   6.250   0.6863   0.01656   0.00886   0.0017   0.1321   0.9796
   6.500   0.7183   0.01787   0.00993  -0.0005   0.0946   0.9870
   6.750   0.7514   0.01911   0.01104  -0.0028   0.0782   0.9946
   7.000   0.7853   0.02009   0.01203  -0.0052   0.0684   1.0000
   7.250   0.7776   0.02076   0.01261   0.0004   0.0652   1.0000
   7.500   0.7786   0.02108   0.01300   0.0048   0.0622   1.0000
   7.750   0.7829   0.02163   0.01354   0.0086   0.0592   1.0000
   8.000   0.7899   0.02242   0.01426   0.0118   0.0566   1.0000
   8.250   0.8026   0.02356   0.01537   0.0141   0.0541   1.0000
   8.500   0.8185   0.02433   0.01622   0.0159   0.0517   1.0000
   8.750   0.8353   0.02515   0.01704   0.0174   0.0492   1.0000
   9.000   0.8561   0.02639   0.01819   0.0181   0.0471   1.0000
   9.250   0.8814   0.02805   0.01992   0.0182   0.0456   1.0000
   9.500   0.9026   0.02930   0.02134   0.0191   0.0445   1.0000
   9.750   0.9241   0.03079   0.02299   0.0199   0.0434   1.0000
  10.000   0.9440   0.03230   0.02464   0.0207   0.0423   1.0000
  10.250   0.9630   0.03368   0.02612   0.0216   0.0411   1.0000
  10.500   0.9806   0.03515   0.02766   0.0225   0.0400   1.0000
  10.750   1.0011   0.03759   0.03017   0.0227   0.0391   1.0000
  11.000   1.0165   0.04103   0.03385   0.0235   0.0387   1.0000
  11.250   1.0235   0.04368   0.03678   0.0255   0.0386   1.0000
  11.500   1.0276   0.04643   0.03982   0.0276   0.0386   1.0000
  11.750   1.0303   0.04978   0.04342   0.0296   0.0387   1.0000
  12.000   1.0294   0.05234   0.04624   0.0320   0.0388   1.0000
  12.250   1.0210   0.05443   0.04857   0.0353   0.0390   1.0000
  12.500   1.0039   0.05679   0.05124   0.0386   0.0394   1.0000
  12.750   0.9101   0.06640   0.06175   0.0417   0.0430   1.0000
  13.000   0.8838   0.07194   0.06749   0.0409   0.0438   1.0000
  13.250   0.8602   0.07772   0.07342   0.0392   0.0446   1.0000
  13.500   0.8398   0.08376   0.07957   0.0371   0.0453   1.0000
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