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NACA 2408 (naca2408-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 2408 (naca2408-il)
Reynolds number: 500,000
Max Cl/Cd: 67.51 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2408-il-500000-n5.txt
Download as CSV file: xf-naca2408-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2408                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5791   0.11822   0.11586   0.0023   1.0000   0.0067
 -11.000  -0.5806   0.11304   0.11070   0.0002   1.0000   0.0068
 -10.500  -0.8500   0.03401   0.03087  -0.0518   1.0000   0.0059
 -10.250  -0.8446   0.02992   0.02640  -0.0521   1.0000   0.0060
 -10.000  -0.8315   0.02744   0.02364  -0.0517   1.0000   0.0062
  -9.750  -0.8151   0.02561   0.02159  -0.0511   1.0000   0.0064
  -9.500  -0.7974   0.02404   0.01982  -0.0504   1.0000   0.0066
  -9.250  -0.7791   0.02260   0.01818  -0.0496   1.0000   0.0068
  -9.000  -0.7604   0.02124   0.01662  -0.0487   1.0000   0.0071
  -8.750  -0.7409   0.01999   0.01516  -0.0477   1.0000   0.0074
  -8.500  -0.7206   0.01893   0.01391  -0.0468   1.0000   0.0078
  -8.250  -0.6997   0.01803   0.01280  -0.0458   1.0000   0.0082
  -8.000  -0.6796   0.01690   0.01150  -0.0448   1.0000   0.0086
  -7.750  -0.6585   0.01605   0.01053  -0.0439   1.0000   0.0092
  -7.500  -0.6367   0.01540   0.00978  -0.0429   1.0000   0.0097
  -7.250  -0.6147   0.01478   0.00906  -0.0420   1.0000   0.0103
  -7.000  -0.5840   0.01409   0.00825  -0.0429   0.9984   0.0111
  -6.750  -0.5521   0.01350   0.00752  -0.0440   0.9964   0.0118
  -6.500  -0.5199   0.01282   0.00677  -0.0453   0.9947   0.0137
  -6.250  -0.4884   0.01243   0.00636  -0.0462   0.9921   0.0154
  -6.000  -0.4560   0.01202   0.00586  -0.0473   0.9895   0.0171
  -5.750  -0.4226   0.01158   0.00541  -0.0487   0.9871   0.0200
  -5.500  -0.3888   0.01134   0.00515  -0.0501   0.9843   0.0234
  -5.250  -0.3557   0.01115   0.00488  -0.0513   0.9802   0.0255
  -5.000  -0.3225   0.01067   0.00437  -0.0525   0.9768   0.0287
  -4.750  -0.2918   0.01042   0.00410  -0.0532   0.9718   0.0315
  -4.500  -0.2604   0.01018   0.00381  -0.0540   0.9669   0.0337
  -4.250  -0.2291   0.00997   0.00354  -0.0548   0.9620   0.0352
  -4.000  -0.1997   0.00961   0.00314  -0.0551   0.9551   0.0379
  -3.750  -0.1693   0.00932   0.00284  -0.0556   0.9490   0.0408
  -3.500  -0.1406   0.00909   0.00258  -0.0557   0.9408   0.0438
  -3.250  -0.1116   0.00890   0.00235  -0.0559   0.9326   0.0468
  -3.000  -0.0832   0.00866   0.00212  -0.0559   0.9232   0.0554
  -2.750  -0.0556   0.00844   0.00194  -0.0558   0.9124   0.0715
  -2.500  -0.0282   0.00822   0.00178  -0.0556   0.9010   0.0943
  -2.250  -0.0009   0.00803   0.00164  -0.0554   0.8888   0.1192
  -2.000   0.0262   0.00785   0.00151  -0.0552   0.8754   0.1484
  -1.750   0.0532   0.00768   0.00140  -0.0550   0.8611   0.1808
  -1.500   0.0801   0.00752   0.00132  -0.0547   0.8458   0.2194
  -1.250   0.1069   0.00733   0.00124  -0.0545   0.8296   0.2713
  -1.000   0.1335   0.00712   0.00118  -0.0542   0.8128   0.3351
  -0.750   0.1593   0.00676   0.00113  -0.0540   0.7949   0.4474
  -0.500   0.1846   0.00638   0.00112  -0.0535   0.7767   0.5784
  -0.250   0.2100   0.00615   0.00111  -0.0529   0.7573   0.6675
   0.000   0.2339   0.00591   0.00114  -0.0519   0.7375   0.7672
   0.250   0.2554   0.00569   0.00119  -0.0500   0.7172   0.8755
   0.500   0.2855   0.00569   0.00121  -0.0500   0.6940   0.9491
   0.750   0.3220   0.00587   0.00120  -0.0519   0.6513   0.9843
   1.000   0.3552   0.00611   0.00121  -0.0531   0.6056   1.0000
   1.250   0.3806   0.00631   0.00125  -0.0526   0.5706   1.0000
   1.500   0.4061   0.00653   0.00130  -0.0521   0.5351   1.0000
   1.750   0.4317   0.00676   0.00137  -0.0516   0.5004   1.0000
   2.000   0.4575   0.00700   0.00145  -0.0513   0.4650   1.0000
   2.250   0.4831   0.00726   0.00155  -0.0509   0.4261   1.0000
   2.500   0.5086   0.00757   0.00167  -0.0505   0.3816   1.0000
   2.750   0.5340   0.00791   0.00181  -0.0501   0.3345   1.0000
   3.000   0.5588   0.00835   0.00199  -0.0497   0.2771   1.0000
   3.250   0.5822   0.00903   0.00229  -0.0491   0.1900   1.0000
   3.500   0.6065   0.00959   0.00257  -0.0487   0.1297   1.0000
   3.750   0.6312   0.01010   0.00286  -0.0483   0.0852   1.0000
   4.000   0.6562   0.01057   0.00316  -0.0479   0.0481   1.0000
   4.250   0.6821   0.01088   0.00343  -0.0476   0.0406   1.0000
   4.500   0.7084   0.01113   0.00369  -0.0473   0.0372   1.0000
   4.750   0.7347   0.01139   0.00398  -0.0470   0.0360   1.0000
   5.000   0.7608   0.01167   0.00432  -0.0467   0.0348   1.0000
   5.250   0.7867   0.01198   0.00467  -0.0464   0.0334   1.0000
   5.500   0.8121   0.01235   0.00507  -0.0460   0.0315   1.0000
   5.750   0.8371   0.01279   0.00555  -0.0456   0.0295   1.0000
   6.000   0.8608   0.01342   0.00627  -0.0449   0.0271   1.0000
   6.250   0.8863   0.01374   0.00662  -0.0446   0.0264   1.0000
   6.500   0.9118   0.01404   0.00697  -0.0443   0.0254   1.0000
   6.750   0.9369   0.01439   0.00738  -0.0439   0.0239   1.0000
   7.000   0.9619   0.01475   0.00779  -0.0435   0.0220   1.0000
   7.250   0.9865   0.01515   0.00823  -0.0431   0.0202   1.0000
   7.500   1.0089   0.01586   0.00897  -0.0423   0.0179   1.0000
   7.750   1.0344   0.01611   0.00928  -0.0420   0.0168   1.0000
   8.000   1.0590   0.01645   0.00967  -0.0416   0.0149   1.0000
   8.250   1.0833   0.01684   0.01007  -0.0412   0.0133   1.0000
   8.500   1.1056   0.01750   0.01074  -0.0405   0.0117   1.0000
   8.750   1.1281   0.01810   0.01145  -0.0397   0.0109   1.0000
   9.000   1.1506   0.01867   0.01209  -0.0391   0.0099   1.0000
   9.250   1.1728   0.01926   0.01271  -0.0384   0.0090   1.0000
   9.500   1.1920   0.02022   0.01374  -0.0373   0.0080   1.0000
   9.750   1.2120   0.02104   0.01469  -0.0363   0.0077   1.0000
  10.000   1.2311   0.02194   0.01572  -0.0352   0.0073   1.0000
  10.250   1.2494   0.02289   0.01679  -0.0340   0.0069   1.0000
  10.500   1.2671   0.02387   0.01788  -0.0328   0.0066   1.0000
  10.750   1.2840   0.02487   0.01900  -0.0315   0.0063   1.0000
  11.000   1.2996   0.02594   0.02022  -0.0301   0.0060   1.0000
  11.250   1.3122   0.02726   0.02165  -0.0284   0.0057   1.0000
  11.500   1.3202   0.02895   0.02351  -0.0262   0.0054   1.0000
  11.750   1.3294   0.03022   0.02495  -0.0240   0.0053   1.0000
  12.000   1.3360   0.03164   0.02654  -0.0217   0.0051   1.0000
  12.250   1.3405   0.03323   0.02831  -0.0194   0.0050   1.0000
  12.500   1.3432   0.03502   0.03027  -0.0172   0.0048   1.0000
  12.750   1.3435   0.03711   0.03254  -0.0154   0.0047   1.0000
  13.000   1.3421   0.03949   0.03511  -0.0139   0.0046   1.0000
  13.250   1.3385   0.04229   0.03809  -0.0129   0.0045   1.0000
  13.500   1.3331   0.04554   0.04153  -0.0126   0.0044   1.0000
  13.750   1.3260   0.04929   0.04546  -0.0130   0.0044   1.0000
  14.000   1.3162   0.05377   0.05014  -0.0142   0.0043   1.0000
  14.250   1.3043   0.05896   0.05551  -0.0163   0.0043   1.0000
  14.500   1.2891   0.06515   0.06189  -0.0194   0.0043   1.0000
  14.750   1.2700   0.07247   0.06941  -0.0234   0.0043   1.0000
  15.000   1.2463   0.08113   0.07826  -0.0284   0.0043   1.0000
  15.250   1.2165   0.09154   0.08888  -0.0344   0.0043   1.0000
  15.500   1.1795   0.10425   0.10178  -0.0415   0.0044   1.0000
  15.750   1.1316   0.12048   0.11821  -0.0502   0.0046   1.0000
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