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NACA 0008 (naca0008-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0008 (naca0008-il)
Reynolds number: 500,000
Max Cl/Cd: 50.19 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0008-il-500000.txt
Download as CSV file: xf-naca0008-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0008                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.9223   0.05195   0.04936  -0.0182   1.0000   0.0104
 -10.500  -0.9411   0.04749   0.04468  -0.0183   1.0000   0.0104
 -10.250  -0.9556   0.04279   0.03965  -0.0172   1.0000   0.0103
 -10.000  -0.9645   0.03782   0.03427  -0.0157   1.0000   0.0104
  -9.750  -0.9671   0.03305   0.02904  -0.0140   1.0000   0.0105
  -9.500  -0.9605   0.02943   0.02502  -0.0125   1.0000   0.0108
  -9.250  -0.9448   0.02751   0.02289  -0.0115   1.0000   0.0112
  -9.000  -0.9238   0.02675   0.02204  -0.0110   1.0000   0.0119
  -8.750  -0.9034   0.02563   0.02077  -0.0103   1.0000   0.0126
  -8.500  -0.8839   0.02395   0.01886  -0.0094   1.0000   0.0133
  -8.250  -0.8640   0.02214   0.01678  -0.0083   1.0000   0.0139
  -8.000  -0.8422   0.02077   0.01520  -0.0075   1.0000   0.0145
  -7.750  -0.8201   0.01943   0.01363  -0.0066   1.0000   0.0151
  -7.500  -0.8022   0.01694   0.01091  -0.0053   1.0000   0.0170
  -7.250  -0.7771   0.01661   0.01055  -0.0049   1.0000   0.0188
  -7.000  -0.7525   0.01604   0.00990  -0.0044   1.0000   0.0208
  -6.750  -0.7273   0.01558   0.00935  -0.0038   1.0000   0.0226
  -6.500  -0.7060   0.01420   0.00787  -0.0028   1.0000   0.0257
  -6.250  -0.6807   0.01388   0.00752  -0.0024   1.0000   0.0292
  -6.000  -0.6549   0.01364   0.00722  -0.0020   1.0000   0.0322
  -5.750  -0.6328   0.01260   0.00612  -0.0011   1.0000   0.0361
  -5.500  -0.6080   0.01224   0.00575  -0.0006   1.0000   0.0396
  -5.250  -0.5831   0.01190   0.00536   0.0000   1.0000   0.0421
  -5.000  -0.5583   0.01159   0.00498   0.0006   1.0000   0.0438
  -4.750  -0.5354   0.01089   0.00423   0.0015   1.0000   0.0473
  -4.500  -0.5111   0.01051   0.00384   0.0022   1.0000   0.0508
  -4.250  -0.4865   0.01020   0.00350   0.0029   1.0000   0.0545
  -4.000  -0.4623   0.00978   0.00309   0.0036   1.0000   0.0622
  -3.750  -0.4382   0.00933   0.00274   0.0043   1.0000   0.0848
  -3.500  -0.4153   0.00865   0.00243   0.0050   1.0000   0.1594
  -3.250  -0.3916   0.00813   0.00222   0.0056   1.0000   0.2319
  -3.000  -0.3676   0.00770   0.00205   0.0061   1.0000   0.3013
  -2.750  -0.3432   0.00732   0.00192   0.0066   1.0000   0.3687
  -2.500  -0.3186   0.00698   0.00183   0.0070   1.0000   0.4337
  -2.250  -0.2937   0.00668   0.00176   0.0075   1.0000   0.4974
  -2.000  -0.2688   0.00636   0.00173   0.0079   1.0000   0.5690
  -1.750  -0.2437   0.00610   0.00172   0.0084   1.0000   0.6356
  -1.500  -0.2147   0.00584   0.00173   0.0081   0.9986   0.7048
  -1.250  -0.1771   0.00557   0.00175   0.0061   0.9942   0.7774
  -1.000  -0.1420   0.00536   0.00179   0.0049   0.9882   0.8432
  -0.750  -0.1059   0.00527   0.00183   0.0035   0.9823   0.8865
  -0.500  -0.0686   0.00523   0.00185   0.0019   0.9757   0.9140
  -0.250  -0.0346   0.00521   0.00185   0.0010   0.9651   0.9359
   0.000   0.0000   0.00521   0.00186   0.0000   0.9521   0.9521
   0.250   0.0346   0.00521   0.00185  -0.0010   0.9359   0.9651
   0.500   0.0686   0.00523   0.00185  -0.0019   0.9139   0.9757
   0.750   0.1059   0.00527   0.00183  -0.0035   0.8865   0.9823
   1.000   0.1420   0.00536   0.00179  -0.0049   0.8433   0.9882
   1.250   0.1771   0.00557   0.00175  -0.0061   0.7780   0.9942
   1.500   0.2147   0.00584   0.00173  -0.0081   0.7047   0.9986
   1.750   0.2437   0.00610   0.00172  -0.0084   0.6347   1.0000
   2.000   0.2688   0.00636   0.00173  -0.0079   0.5686   1.0000
   2.250   0.2937   0.00667   0.00176  -0.0075   0.4978   1.0000
   2.500   0.3186   0.00698   0.00183  -0.0070   0.4337   1.0000
   2.750   0.3432   0.00732   0.00192  -0.0066   0.3688   1.0000
   3.000   0.3676   0.00770   0.00205  -0.0061   0.3011   1.0000
   3.250   0.3917   0.00814   0.00222  -0.0056   0.2317   1.0000
   3.500   0.4153   0.00865   0.00243  -0.0050   0.1594   1.0000
   3.750   0.4382   0.00933   0.00274  -0.0043   0.0848   1.0000
   4.000   0.4623   0.00978   0.00309  -0.0036   0.0622   1.0000
   4.250   0.4865   0.01020   0.00350  -0.0029   0.0545   1.0000
   4.500   0.5111   0.01050   0.00384  -0.0022   0.0509   1.0000
   4.750   0.5354   0.01089   0.00423  -0.0015   0.0473   1.0000
   5.000   0.5584   0.01159   0.00498  -0.0006   0.0438   1.0000
   5.250   0.5832   0.01190   0.00536   0.0000   0.0421   1.0000
   5.500   0.6081   0.01224   0.00575   0.0006   0.0396   1.0000
   5.750   0.6329   0.01261   0.00613   0.0011   0.0361   1.0000
   6.000   0.6550   0.01364   0.00722   0.0020   0.0322   1.0000
   6.250   0.6807   0.01388   0.00753   0.0024   0.0292   1.0000
   6.500   0.7060   0.01420   0.00787   0.0028   0.0257   1.0000
   6.750   0.7273   0.01557   0.00934   0.0038   0.0226   1.0000
   7.000   0.7525   0.01604   0.00990   0.0044   0.0209   1.0000
   7.250   0.7771   0.01660   0.01055   0.0049   0.0188   1.0000
   7.500   0.8022   0.01694   0.01091   0.0053   0.0170   1.0000
   7.750   0.8201   0.01942   0.01362   0.0066   0.0151   1.0000
   8.000   0.8422   0.02077   0.01520   0.0075   0.0145   1.0000
   8.250   0.8640   0.02214   0.01679   0.0083   0.0139   1.0000
   8.500   0.8838   0.02396   0.01887   0.0094   0.0133   1.0000
   8.750   0.9034   0.02562   0.02076   0.0103   0.0126   1.0000
   9.000   0.9238   0.02675   0.02204   0.0110   0.0119   1.0000
   9.250   0.9448   0.02749   0.02287   0.0115   0.0112   1.0000
   9.500   0.9604   0.02942   0.02502   0.0125   0.0108   1.0000
   9.750   0.9670   0.03306   0.02905   0.0140   0.0105   1.0000
  10.000   0.9646   0.03780   0.03425   0.0157   0.0104   1.0000
  10.250   0.9555   0.04282   0.03968   0.0172   0.0103   1.0000
  10.500   0.9412   0.04751   0.04469   0.0182   0.0104   1.0000
  10.750   0.9221   0.05202   0.04944   0.0181   0.0104   1.0000
  11.000   0.8994   0.05928   0.05694   0.0122   0.0106   1.0000
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