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NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-108 AIRFOIL (n64108-il)
Reynolds number: 1,000,000
Max Cl/Cd: 63.12 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64108-il-1000000.txt
Download as CSV file: xf-n64108-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-108 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6147   0.08216   0.08058  -0.0092   1.0000   0.0090
  -9.000  -0.6205   0.07484   0.07330  -0.0154   1.0000   0.0090
  -8.750  -0.6317   0.06835   0.06678  -0.0216   1.0000   0.0090
  -8.500  -0.6461   0.06398   0.06235  -0.0233   1.0000   0.0090
  -8.250  -0.6518   0.05908   0.05733  -0.0246   1.0000   0.0090
  -8.000  -0.6541   0.05404   0.05215  -0.0254   1.0000   0.0090
  -7.750  -0.6527   0.04905   0.04698  -0.0256   1.0000   0.0090
  -7.500  -0.6650   0.03944   0.03696  -0.0254   1.0000   0.0092
  -7.000  -0.6553   0.02622   0.02284  -0.0233   1.0000   0.0075
  -6.750  -0.6405   0.02033   0.01631  -0.0216   1.0000   0.0081
  -6.500  -0.6177   0.01850   0.01423  -0.0209   1.0000   0.0086
  -6.250  -0.5928   0.01782   0.01340  -0.0205   1.0000   0.0089
  -6.000  -0.5729   0.01452   0.00969  -0.0194   1.0000   0.0093
  -5.750  -0.5510   0.01285   0.00788  -0.0186   1.0000   0.0101
  -5.500  -0.5267   0.01260   0.00763  -0.0181   1.0000   0.0110
  -5.250  -0.4998   0.01210   0.00708  -0.0182   0.9984   0.0120
  -5.000  -0.4664   0.01130   0.00620  -0.0196   0.9927   0.0128
  -4.750  -0.4326   0.01067   0.00550  -0.0210   0.9866   0.0135
  -4.500  -0.3983   0.01024   0.00502  -0.0226   0.9799   0.0140
  -4.250  -0.3673   0.00888   0.00352  -0.0237   0.9699   0.0161
  -4.000  -0.3376   0.00855   0.00316  -0.0242   0.9577   0.0179
  -3.750  -0.3105   0.00826   0.00280  -0.0240   0.9443   0.0194
  -3.500  -0.2845   0.00804   0.00251  -0.0235   0.9312   0.0208
  -3.250  -0.2586   0.00772   0.00209  -0.0231   0.9186   0.0239
  -3.000  -0.2323   0.00749   0.00184  -0.0227   0.9067   0.0311
  -2.750  -0.2059   0.00726   0.00160  -0.0224   0.8950   0.0433
  -2.500  -0.1800   0.00680   0.00136  -0.0222   0.8837   0.1172
  -2.250  -0.1555   0.00589   0.00108  -0.0222   0.8725   0.3105
  -2.000  -0.1306   0.00509   0.00091  -0.0221   0.8614   0.5037
  -1.750  -0.1040   0.00482   0.00086  -0.0219   0.8506   0.5815
  -1.500  -0.0768   0.00472   0.00081  -0.0218   0.8399   0.6163
  -1.250  -0.0495   0.00465   0.00077  -0.0217   0.8292   0.6460
  -1.000  -0.0224   0.00455   0.00077  -0.0215   0.8185   0.6859
  -0.750   0.0046   0.00447   0.00078  -0.0213   0.8079   0.7259
  -0.500   0.0321   0.00445   0.00078  -0.0211   0.7973   0.7489
  -0.250   0.0597   0.00444   0.00078  -0.0210   0.7865   0.7636
   0.000   0.0875   0.00445   0.00078  -0.0209   0.7756   0.7763
   0.250   0.1152   0.00445   0.00079  -0.0209   0.7638   0.7874
   0.500   0.1428   0.00446   0.00080  -0.0208   0.7507   0.7986
   0.750   0.1702   0.00450   0.00081  -0.0206   0.7339   0.8098
   1.000   0.1974   0.00455   0.00082  -0.0204   0.7087   0.8210
   1.250   0.2242   0.00465   0.00083  -0.0202   0.6730   0.8323
   1.500   0.2509   0.00476   0.00087  -0.0199   0.6390   0.8437
   1.750   0.2778   0.00484   0.00092  -0.0197   0.6115   0.8553
   2.000   0.3045   0.00496   0.00099  -0.0194   0.5786   0.8668
   2.250   0.3301   0.00523   0.00107  -0.0190   0.5136   0.8786
   2.500   0.3541   0.00579   0.00123  -0.0185   0.3884   0.8909
   2.750   0.3756   0.00685   0.00158  -0.0179   0.1934   0.9044
   3.000   0.3982   0.00763   0.00190  -0.0172   0.0641   0.9186
   3.250   0.4225   0.00795   0.00213  -0.0165   0.0353   0.9333
   3.500   0.4471   0.00811   0.00233  -0.0157   0.0290   0.9497
   3.750   0.4738   0.00844   0.00272  -0.0154   0.0223   0.9687
   4.000   0.5078   0.00869   0.00301  -0.0169   0.0196   0.9871
   4.250   0.5379   0.00905   0.00338  -0.0176   0.0173   1.0000
   4.500   0.5623   0.00997   0.00441  -0.0171   0.0149   1.0000
   4.750   0.5888   0.01038   0.00485  -0.0170   0.0145   1.0000
   5.000   0.6148   0.01089   0.00543  -0.0167   0.0140   1.0000
   5.250   0.6404   0.01148   0.00608  -0.0165   0.0134   1.0000
   5.500   0.6660   0.01209   0.00674  -0.0162   0.0126   1.0000
   5.750   0.6922   0.01250   0.00717  -0.0160   0.0116   1.0000
   6.000   0.7178   0.01299   0.00766  -0.0159   0.0106   1.0000
   6.250   0.7375   0.01575   0.01067  -0.0146   0.0097   1.0000
   6.500   0.7621   0.01693   0.01200  -0.0142   0.0094   1.0000
   6.750   0.7874   0.01766   0.01284  -0.0139   0.0090   1.0000
   7.000   0.8115   0.01895   0.01431  -0.0133   0.0086   1.0000
   7.250   0.8343   0.02067   0.01626  -0.0126   0.0079   1.0000
   7.500   0.8546   0.02314   0.01902  -0.0117   0.0075   1.0000
   7.750   0.8786   0.02345   0.01938  -0.0115   0.0070   1.0000
   8.000   0.9022   0.02373   0.01973  -0.0114   0.0067   1.0000
   8.250   0.9215   0.02535   0.02153  -0.0107   0.0064   1.0000
   8.500   0.9275   0.03064   0.02737  -0.0087   0.0062   1.0000
  10.500   0.6510   0.10102   0.09965  -0.0257   0.0096   1.0000
  10.750   0.6461   0.10754   0.10616  -0.0286   0.0096   1.0000
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