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NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-208 (naca64208-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.81 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64208-il-1000000.txt
Download as CSV file: xf-naca64208-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-208                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4791   0.09407   0.09254  -0.0105   1.0000   0.0088
 -10.000  -0.4811   0.08900   0.08747  -0.0124   1.0000   0.0088
  -9.750  -0.4837   0.08385   0.08233  -0.0143   1.0000   0.0089
  -9.500  -0.4856   0.07912   0.07762  -0.0162   1.0000   0.0090
  -9.250  -0.4888   0.07423   0.07274  -0.0181   1.0000   0.0091
  -9.000  -0.4940   0.06886   0.06738  -0.0205   1.0000   0.0092
  -8.750  -0.5041   0.06232   0.06086  -0.0241   1.0000   0.0091
  -8.500  -0.5291   0.05262   0.05116  -0.0329   1.0000   0.0090
  -6.750  -0.5716   0.02831   0.02530  -0.0367   1.0000   0.0076
  -6.500  -0.5614   0.02236   0.01880  -0.0343   1.0000   0.0081
  -6.250  -0.5381   0.02029   0.01643  -0.0339   0.9991   0.0084
  -6.000  -0.5090   0.01518   0.01064  -0.0353   0.9960   0.0088
  -5.750  -0.4772   0.01340   0.00867  -0.0368   0.9932   0.0095
  -5.500  -0.4442   0.01325   0.00851  -0.0382   0.9895   0.0104
  -5.250  -0.4108   0.01237   0.00753  -0.0396   0.9861   0.0114
  -5.000  -0.3765   0.01153   0.00658  -0.0411   0.9829   0.0123
  -4.750  -0.3452   0.01094   0.00592  -0.0420   0.9760   0.0129
  -4.500  -0.3126   0.01010   0.00499  -0.0432   0.9697   0.0134
  -4.250  -0.2845   0.00889   0.00368  -0.0436   0.9593   0.0154
  -4.000  -0.2559   0.00859   0.00335  -0.0438   0.9484   0.0170
  -3.750  -0.2289   0.00826   0.00294  -0.0436   0.9366   0.0183
  -3.500  -0.2023   0.00801   0.00261  -0.0433   0.9248   0.0194
  -3.000  -0.1493   0.00738   0.00183  -0.0427   0.9020   0.0271
  -2.750  -0.1223   0.00720   0.00158  -0.0425   0.8909   0.0328
  -2.500  -0.0953   0.00697   0.00137  -0.0423   0.8801   0.0494
  -2.250  -0.0689   0.00644   0.00116  -0.0424   0.8696   0.1527
  -2.000  -0.0438   0.00531   0.00090  -0.0427   0.8590   0.4233
  -1.750  -0.0172   0.00489   0.00083  -0.0427   0.8483   0.5460
  -1.500   0.0101   0.00473   0.00080  -0.0426   0.8379   0.6004
  -1.250   0.0376   0.00467   0.00076  -0.0425   0.8275   0.6309
  -1.000   0.0649   0.00458   0.00076  -0.0424   0.8170   0.6718
  -0.750   0.0922   0.00450   0.00077  -0.0422   0.8067   0.7116
  -0.500   0.1196   0.00447   0.00078  -0.0421   0.7964   0.7395
  -0.250   0.1470   0.00447   0.00079  -0.0419   0.7859   0.7627
   0.000   0.1747   0.00447   0.00080  -0.0418   0.7752   0.7759
   0.250   0.2025   0.00448   0.00081  -0.0418   0.7640   0.7875
   0.500   0.2301   0.00449   0.00083  -0.0417   0.7517   0.7991
   0.750   0.2576   0.00452   0.00085  -0.0416   0.7380   0.8106
   1.000   0.2847   0.00458   0.00086  -0.0413   0.7162   0.8221
   1.250   0.3115   0.00467   0.00089  -0.0411   0.6888   0.8336
   1.500   0.3379   0.00479   0.00092  -0.0407   0.6518   0.8456
   1.750   0.3646   0.00488   0.00098  -0.0405   0.6247   0.8575
   2.000   0.3912   0.00498   0.00104  -0.0402   0.5979   0.8694
   2.250   0.4170   0.00516   0.00112  -0.0398   0.5559   0.8816
   2.500   0.4417   0.00548   0.00124  -0.0392   0.4859   0.8943
   2.750   0.4634   0.00626   0.00148  -0.0383   0.3372   0.9085
   3.000   0.4832   0.00733   0.00187  -0.0373   0.1554   0.9243
   3.250   0.5045   0.00802   0.00218  -0.0362   0.0553   0.9416
   3.500   0.5284   0.00829   0.00240  -0.0354   0.0337   0.9625
   4.000   0.5885   0.00890   0.00305  -0.0366   0.0216   1.0000
   4.250   0.6159   0.00919   0.00336  -0.0366   0.0191   1.0000
   4.500   0.6422   0.00967   0.00387  -0.0365   0.0162   1.0000
   4.750   0.6670   0.01046   0.00477  -0.0360   0.0149   1.0000
   5.000   0.6932   0.01090   0.00525  -0.0358   0.0144   1.0000
   5.250   0.7189   0.01143   0.00584  -0.0355   0.0138   1.0000
   5.500   0.7443   0.01203   0.00649  -0.0352   0.0131   1.0000
   5.750   0.7700   0.01254   0.00705  -0.0350   0.0122   1.0000
   6.000   0.7962   0.01292   0.00744  -0.0349   0.0113   1.0000
   6.250   0.8200   0.01385   0.00843  -0.0344   0.0104   1.0000
   6.750   0.8642   0.01748   0.01241  -0.0326   0.0094   1.0000
   7.000   0.8890   0.01836   0.01341  -0.0322   0.0090   1.0000
   7.250   0.9131   0.01950   0.01471  -0.0317   0.0085   1.0000
   7.500   0.9371   0.02039   0.01573  -0.0313   0.0078   1.0000
   7.750   0.9611   0.02103   0.01645  -0.0310   0.0073   1.0000
   8.000   0.9849   0.02153   0.01702  -0.0307   0.0069   1.0000
   8.250   1.0062   0.02282   0.01844  -0.0301   0.0066   1.0000
   8.500   1.0200   0.02620   0.02220  -0.0286   0.0063   1.0000
   8.750   1.0171   0.03328   0.03000  -0.0255   0.0061   1.0000
   9.000   1.0060   0.04076   0.03808  -0.0223   0.0061   1.0000
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