Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.14 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a210-il-1000000.txt
Download as CSV file: xf-naca64a210-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A210                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6615   0.05062   0.04869  -0.0476   1.0000   0.0103
  -8.750  -0.6829   0.04326   0.04105  -0.0462   1.0000   0.0096
  -8.500  -0.7318   0.02588   0.02242  -0.0406   0.9972   0.0093
  -8.250  -0.7071   0.02221   0.01830  -0.0418   0.9948   0.0097
  -8.000  -0.6804   0.01984   0.01561  -0.0427   0.9921   0.0101
  -7.750  -0.6511   0.01829   0.01382  -0.0437   0.9894   0.0105
  -7.500  -0.6188   0.01755   0.01293  -0.0451   0.9873   0.0109
  -7.250  -0.5911   0.01499   0.01010  -0.0461   0.9849   0.0119
  -7.000  -0.5592   0.01444   0.00952  -0.0474   0.9824   0.0125
  -6.750  -0.5314   0.01376   0.00877  -0.0477   0.9769   0.0130
  -6.500  -0.5021   0.01304   0.00796  -0.0483   0.9724   0.0135
  -6.250  -0.4745   0.01237   0.00721  -0.0485   0.9670   0.0141
  -6.000  -0.4486   0.01184   0.00661  -0.0482   0.9599   0.0147
  -5.750  -0.4218   0.01151   0.00622  -0.0480   0.9537   0.0151
  -5.500  -0.4000   0.01041   0.00500  -0.0470   0.9454   0.0164
  -5.250  -0.3749   0.00995   0.00449  -0.0466   0.9384   0.0173
  -5.000  -0.3495   0.00960   0.00410  -0.0462   0.9308   0.0181
  -4.750  -0.3236   0.00928   0.00373  -0.0458   0.9239   0.0191
  -4.500  -0.2975   0.00900   0.00338  -0.0455   0.9164   0.0202
  -4.250  -0.2710   0.00878   0.00312  -0.0452   0.9094   0.0211
  -4.000  -0.2453   0.00834   0.00261  -0.0448   0.9017   0.0246
  -3.750  -0.2185   0.00814   0.00237  -0.0446   0.8946   0.0275
  -3.500  -0.1919   0.00787   0.00208  -0.0444   0.8870   0.0345
  -3.250  -0.1651   0.00763   0.00187  -0.0442   0.8798   0.0498
  -3.000  -0.1389   0.00731   0.00168  -0.0440   0.8718   0.0901
  -2.750  -0.1138   0.00675   0.00147  -0.0438   0.8640   0.1916
  -2.500  -0.0903   0.00597   0.00122  -0.0435   0.8560   0.3539
  -2.250  -0.0658   0.00542   0.00110  -0.0431   0.8475   0.4902
  -2.000  -0.0395   0.00522   0.00105  -0.0429   0.8395   0.5498
  -1.750  -0.0125   0.00509   0.00101  -0.0427   0.8305   0.5906
  -1.500   0.0147   0.00502   0.00097  -0.0426   0.8219   0.6169
  -1.250   0.0420   0.00497   0.00094  -0.0425   0.8126   0.6393
  -1.000   0.0692   0.00490   0.00093  -0.0423   0.8029   0.6680
  -0.750   0.0961   0.00486   0.00093  -0.0421   0.7934   0.6967
  -0.500   0.1234   0.00485   0.00093  -0.0419   0.7838   0.7149
  -0.250   0.1510   0.00484   0.00093  -0.0418   0.7738   0.7296
   0.000   0.1786   0.00485   0.00093  -0.0418   0.7642   0.7417
   0.500   0.2339   0.00487   0.00095  -0.0417   0.7448   0.7630
   0.750   0.2615   0.00489   0.00097  -0.0416   0.7351   0.7733
   1.000   0.2889   0.00492   0.00099  -0.0415   0.7234   0.7838
   1.500   0.3431   0.00497   0.00104  -0.0412   0.6931   0.8071
   1.750   0.3697   0.00500   0.00107  -0.0409   0.6738   0.8199
   2.000   0.3957   0.00507   0.00111  -0.0405   0.6485   0.8349
   2.250   0.4214   0.00513   0.00116  -0.0401   0.6235   0.8539
   2.500   0.4469   0.00517   0.00124  -0.0395   0.6006   0.8798
   2.750   0.4719   0.00522   0.00133  -0.0388   0.5774   0.9144
   3.000   0.5002   0.00539   0.00145  -0.0389   0.5396   0.9522
   3.250   0.5346   0.00574   0.00159  -0.0406   0.4749   0.9759
   3.500   0.5648   0.00675   0.00193  -0.0419   0.3156   0.9919
   3.750   0.5945   0.00777   0.00235  -0.0432   0.1760   1.0000
   4.000   0.6144   0.00842   0.00266  -0.0420   0.1013   1.0000
   4.250   0.6365   0.00889   0.00294  -0.0410   0.0608   1.0000
   4.500   0.6597   0.00929   0.00321  -0.0403   0.0379   1.0000
   4.750   0.6835   0.00965   0.00353  -0.0396   0.0273   1.0000
   5.000   0.7080   0.00997   0.00383  -0.0391   0.0228   1.0000
   5.250   0.7318   0.01039   0.00429  -0.0384   0.0198   1.0000
   5.500   0.7566   0.01070   0.00462  -0.0379   0.0186   1.0000
   5.750   0.7811   0.01105   0.00500  -0.0374   0.0174   1.0000
   6.000   0.8053   0.01145   0.00541  -0.0368   0.0165   1.0000
   6.250   0.8279   0.01204   0.00605  -0.0360   0.0154   1.0000
   6.500   0.8483   0.01290   0.00701  -0.0348   0.0145   1.0000
   6.750   0.8725   0.01329   0.00743  -0.0343   0.0141   1.0000
   7.000   0.8957   0.01383   0.00803  -0.0336   0.0136   1.0000
   7.250   0.9182   0.01445   0.00870  -0.0328   0.0131   1.0000
   7.500   0.9405   0.01511   0.00942  -0.0320   0.0127   1.0000
   7.750   0.9627   0.01579   0.01015  -0.0312   0.0123   1.0000
   8.000   0.9848   0.01648   0.01090  -0.0305   0.0119   1.0000
   8.250   1.0071   0.01713   0.01158  -0.0298   0.0114   1.0000
   8.500   1.0264   0.01829   0.01280  -0.0287   0.0108   1.0000
   8.750   1.0425   0.02054   0.01525  -0.0271   0.0103   1.0000
   9.000   1.0646   0.02117   0.01598  -0.0264   0.0101   1.0000
   9.250   1.0854   0.02210   0.01704  -0.0255   0.0098   1.0000
   9.500   1.1049   0.02329   0.01837  -0.0245   0.0095   1.0000
   9.750   1.1230   0.02466   0.01991  -0.0233   0.0092   1.0000
  10.000   1.1398   0.02612   0.02153  -0.0221   0.0090   1.0000
  10.250   1.1559   0.02744   0.02300  -0.0208   0.0087   1.0000
  10.500   1.1725   0.02837   0.02402  -0.0196   0.0084   1.0000
  10.750   1.1885   0.02912   0.02486  -0.0184   0.0081   1.0000
  11.000   1.2038   0.02983   0.02562  -0.0172   0.0079   1.0000
  11.250   1.2138   0.03114   0.02702  -0.0154   0.0077   1.0000
  11.500   1.2043   0.03460   0.03078  -0.0114   0.0074   1.0000
  12.000   1.1645   0.04270   0.03957  -0.0038   0.0072   1.0000
  12.250   1.1594   0.04522   0.04226  -0.0023   0.0071   1.0000
  12.500   1.1478   0.04871   0.04596  -0.0013   0.0071   1.0000
  12.750   1.1311   0.05319   0.05065  -0.0011   0.0070   1.0000
  13.000   1.1091   0.05888   0.05655  -0.0023   0.0070   1.0000
  13.250   1.0840   0.06581   0.06368  -0.0052   0.0070   1.0000
  13.500   1.0531   0.07474   0.07280  -0.0101   0.0071   1.0000
<< Back to NACA 64A210 (naca64a210-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64A210 (naca64a210-il)