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NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-208 (naca64208-il)
Reynolds number: 500,000
Max Cl/Cd: 60.71 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64208-il-500000-n5.txt
Download as CSV file: xf-naca64208-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5861   0.08522   0.08300  -0.0145   1.0000   0.0052
  -9.250  -0.5943   0.07855   0.07637  -0.0185   1.0000   0.0050
  -9.000  -0.6010   0.07241   0.07027  -0.0231   1.0000   0.0049
  -8.750  -0.6140   0.06560   0.06346  -0.0303   1.0000   0.0049
  -8.500  -0.6266   0.05894   0.05670  -0.0346   1.0000   0.0049
  -8.250  -0.6337   0.05238   0.04996  -0.0371   1.0000   0.0049
  -8.000  -0.6422   0.04382   0.04109  -0.0385   1.0000   0.0049
  -7.750  -0.6452   0.03518   0.03195  -0.0385   1.0000   0.0051
  -7.500  -0.6352   0.02999   0.02637  -0.0378   1.0000   0.0053
  -7.250  -0.6187   0.02708   0.02315  -0.0372   1.0000   0.0056
  -7.000  -0.6032   0.02318   0.01881  -0.0361   1.0000   0.0061
  -6.750  -0.5851   0.02022   0.01543  -0.0349   1.0000   0.0066
  -6.500  -0.5644   0.01851   0.01344  -0.0340   1.0000   0.0073
  -6.250  -0.5339   0.01732   0.01199  -0.0349   0.9958   0.0080
  -6.000  -0.5041   0.01510   0.00943  -0.0359   0.9902   0.0088
  -5.750  -0.4717   0.01429   0.00853  -0.0373   0.9851   0.0095
  -5.500  -0.4398   0.01363   0.00778  -0.0385   0.9787   0.0104
  -5.250  -0.4080   0.01292   0.00697  -0.0396   0.9718   0.0115
  -5.000  -0.3751   0.01253   0.00648  -0.0409   0.9648   0.0128
  -4.750  -0.3443   0.01196   0.00582  -0.0417   0.9556   0.0134
  -4.500  -0.3152   0.01083   0.00457  -0.0423   0.9456   0.0148
  -4.250  -0.2860   0.01036   0.00404  -0.0428   0.9350   0.0161
  -4.000  -0.2580   0.01005   0.00368  -0.0429   0.9236   0.0179
  -3.750  -0.2309   0.00968   0.00320  -0.0428   0.9119   0.0194
  -3.500  -0.2040   0.00940   0.00283  -0.0426   0.9002   0.0211
  -3.250  -0.1772   0.00909   0.00244  -0.0424   0.8887   0.0240
  -3.000  -0.1503   0.00885   0.00216  -0.0422   0.8777   0.0293
  -2.750  -0.1233   0.00870   0.00194  -0.0420   0.8670   0.0347
  -2.500  -0.0964   0.00847   0.00172  -0.0419   0.8562   0.0521
  -2.250  -0.0697   0.00805   0.00152  -0.0419   0.8453   0.1206
  -2.000  -0.0440   0.00722   0.00127  -0.0421   0.8348   0.3009
  -1.750  -0.0181   0.00657   0.00112  -0.0422   0.8248   0.4659
  -1.500   0.0086   0.00629   0.00106  -0.0421   0.8146   0.5490
  -1.250   0.0347   0.00601   0.00109  -0.0418   0.8041   0.6463
  -1.000   0.0612   0.00589   0.00111  -0.0414   0.7939   0.6970
  -0.750   0.0882   0.00586   0.00110  -0.0412   0.7842   0.7224
  -0.500   0.1159   0.00585   0.00108  -0.0411   0.7741   0.7346
  -0.250   0.1436   0.00586   0.00107  -0.0410   0.7640   0.7452
   0.000   0.1712   0.00587   0.00107  -0.0409   0.7540   0.7559
   0.250   0.1987   0.00589   0.00108  -0.0408   0.7442   0.7668
   0.500   0.2264   0.00590   0.00111  -0.0407   0.7344   0.7778
   0.750   0.2540   0.00592   0.00114  -0.0406   0.7247   0.7885
   1.250   0.3080   0.00602   0.00122  -0.0402   0.6917   0.8112
   1.500   0.3343   0.00612   0.00126  -0.0397   0.6639   0.8226
   1.750   0.3601   0.00626   0.00131  -0.0393   0.6276   0.8339
   2.000   0.3849   0.00652   0.00136  -0.0386   0.5671   0.8455
   2.250   0.4096   0.00680   0.00148  -0.0380   0.5071   0.8578
   2.500   0.4341   0.00715   0.00162  -0.0374   0.4375   0.8705
   2.750   0.4534   0.00832   0.00201  -0.0364   0.2364   0.8844
   3.000   0.4744   0.00923   0.00238  -0.0356   0.0997   0.8991
   3.250   0.4979   0.00965   0.00264  -0.0348   0.0531   0.9148
   3.500   0.5221   0.00989   0.00290  -0.0340   0.0380   0.9321
   3.750   0.5477   0.01013   0.00315  -0.0336   0.0305   0.9524
   4.000   0.5790   0.01039   0.00345  -0.0345   0.0248   0.9789
   4.250   0.6075   0.01070   0.00378  -0.0349   0.0209   1.0000
   4.500   0.6337   0.01116   0.00428  -0.0347   0.0179   1.0000
   4.750   0.6592   0.01171   0.00490  -0.0344   0.0165   1.0000
   5.000   0.6852   0.01216   0.00542  -0.0342   0.0158   1.0000
   5.250   0.7106   0.01271   0.00603  -0.0339   0.0149   1.0000
   5.500   0.7356   0.01331   0.00670  -0.0336   0.0140   1.0000
   5.750   0.7611   0.01379   0.00723  -0.0334   0.0129   1.0000
   6.000   0.7860   0.01438   0.00789  -0.0331   0.0121   1.0000
   6.250   0.8103   0.01513   0.00870  -0.0326   0.0114   1.0000
   6.500   0.8322   0.01644   0.01013  -0.0319   0.0105   1.0000
   6.750   0.8561   0.01738   0.01118  -0.0314   0.0098   1.0000
   7.000   0.8810   0.01796   0.01186  -0.0311   0.0092   1.0000
   7.250   0.9047   0.01898   0.01303  -0.0306   0.0085   1.0000
   7.500   0.9281   0.02002   0.01422  -0.0301   0.0079   1.0000
   7.750   0.9513   0.02096   0.01532  -0.0296   0.0073   1.0000
   8.000   0.9745   0.02176   0.01622  -0.0292   0.0069   1.0000
   8.250   0.9963   0.02277   0.01735  -0.0287   0.0064   1.0000
   8.500   1.0139   0.02519   0.02010  -0.0277   0.0059   1.0000
   8.750   1.0341   0.02677   0.02196  -0.0269   0.0055   1.0000
   9.000   1.0489   0.02969   0.02528  -0.0255   0.0050   1.0000
   9.250   1.0514   0.03536   0.03159  -0.0231   0.0046   1.0000
   9.500   1.0268   0.04658   0.04360  -0.0190   0.0043   1.0000
   9.750   1.0089   0.05396   0.05136  -0.0167   0.0042   1.0000
  10.000   0.9851   0.05990   0.05755  -0.0145   0.0041   1.0000
  10.250   0.9557   0.06533   0.06314  -0.0134   0.0042   1.0000
  10.500   0.9218   0.07285   0.07081  -0.0163   0.0043   1.0000
  10.750   0.8882   0.08400   0.08207  -0.0246   0.0045   1.0000
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