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

NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 500,000
Max Cl/Cd: 63.2 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64210-il-500000-n5.txt
Download as CSV file: xf-naca64210-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-210                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6176   0.09870   0.09637  -0.0141   1.0000   0.0079
 -11.250  -0.6442   0.08740   0.08512  -0.0202   1.0000   0.0080
 -10.250  -0.8560   0.03394   0.03043  -0.0427   1.0000   0.0077
 -10.000  -0.8576   0.02952   0.02547  -0.0411   1.0000   0.0080
  -9.750  -0.8501   0.02640   0.02196  -0.0399   1.0000   0.0082
  -9.500  -0.8336   0.02495   0.02034  -0.0391   1.0000   0.0085
  -9.250  -0.8141   0.02401   0.01930  -0.0385   1.0000   0.0088
  -9.000  -0.7944   0.02304   0.01820  -0.0379   1.0000   0.0091
  -8.750  -0.7738   0.02222   0.01725  -0.0372   1.0000   0.0095
  -8.500  -0.7536   0.02126   0.01615  -0.0365   1.0000   0.0100
  -8.250  -0.7341   0.02012   0.01482  -0.0355   1.0000   0.0106
  -8.000  -0.7099   0.01909   0.01361  -0.0354   0.9973   0.0111
  -7.750  -0.6790   0.01804   0.01237  -0.0367   0.9896   0.0114
  -7.500  -0.6493   0.01660   0.01079  -0.0379   0.9813   0.0122
  -7.250  -0.6173   0.01587   0.00998  -0.0394   0.9731   0.0127
  -7.000  -0.5851   0.01532   0.00935  -0.0407   0.9642   0.0134
  -6.750  -0.5542   0.01474   0.00870  -0.0417   0.9541   0.0143
  -6.500  -0.5249   0.01416   0.00802  -0.0424   0.9431   0.0150
  -6.250  -0.4975   0.01357   0.00731  -0.0425   0.9313   0.0156
  -6.000  -0.4714   0.01308   0.00671  -0.0423   0.9194   0.0159
  -5.750  -0.4475   0.01229   0.00584  -0.0418   0.9071   0.0170
  -5.500  -0.4221   0.01192   0.00542  -0.0415   0.8956   0.0181
  -5.250  -0.3963   0.01159   0.00503  -0.0413   0.8845   0.0192
  -5.000  -0.3706   0.01123   0.00457  -0.0409   0.8742   0.0204
  -4.750  -0.3446   0.01091   0.00417  -0.0407   0.8636   0.0215
  -4.500  -0.3182   0.01062   0.00380  -0.0405   0.8533   0.0227
  -4.250  -0.2920   0.01024   0.00337  -0.0403   0.8436   0.0255
  -3.750  -0.2380   0.00985   0.00284  -0.0401   0.8244   0.0312
  -3.500  -0.2111   0.00959   0.00256  -0.0400   0.8153   0.0376
  -3.250  -0.1838   0.00941   0.00234  -0.0399   0.8062   0.0442
  -3.000  -0.1567   0.00913   0.00213  -0.0399   0.7974   0.0665
  -2.750  -0.1302   0.00870   0.00190  -0.0400   0.7886   0.1306
  -2.500  -0.1043   0.00797   0.00162  -0.0402   0.7793   0.2629
  -2.250  -0.0787   0.00721   0.00139  -0.0404   0.7706   0.4228
  -2.000  -0.0515   0.00696   0.00132  -0.0404   0.7621   0.4909
  -1.750  -0.0242   0.00677   0.00128  -0.0404   0.7537   0.5489
  -1.500   0.0028   0.00660   0.00130  -0.0403   0.7456   0.6108
  -1.250   0.0303   0.00654   0.00130  -0.0402   0.7368   0.6466
  -1.000   0.0582   0.00652   0.00128  -0.0401   0.7284   0.6614
  -0.750   0.0864   0.00652   0.00126  -0.0402   0.7199   0.6709
  -0.500   0.1146   0.00652   0.00124  -0.0402   0.7122   0.6786
  -0.250   0.1428   0.00653   0.00123  -0.0403   0.7044   0.6868
   0.000   0.1710   0.00654   0.00124  -0.0404   0.6967   0.6950
   0.250   0.1992   0.00657   0.00124  -0.0404   0.6888   0.7037
   0.500   0.2274   0.00657   0.00127  -0.0405   0.6808   0.7116
   1.000   0.2837   0.00662   0.00135  -0.0406   0.6662   0.7287
   1.250   0.3116   0.00666   0.00140  -0.0406   0.6580   0.7377
   1.500   0.3396   0.00670   0.00145  -0.0406   0.6475   0.7471
   1.750   0.3672   0.00675   0.00151  -0.0405   0.6337   0.7559
   2.000   0.3942   0.00684   0.00157  -0.0403   0.6081   0.7649
   2.250   0.4202   0.00701   0.00162  -0.0399   0.5683   0.7742
   2.500   0.4463   0.00721   0.00170  -0.0396   0.5276   0.7836
   2.750   0.4721   0.00747   0.00182  -0.0393   0.4772   0.7936
   3.250   0.5181   0.00879   0.00238  -0.0381   0.2709   0.8133
   3.500   0.5407   0.00958   0.00277  -0.0376   0.1696   0.8235
   3.750   0.5635   0.01030   0.00316  -0.0371   0.0876   0.8345
   4.000   0.5878   0.01075   0.00348  -0.0366   0.0511   0.8452
   4.250   0.6129   0.01105   0.00377  -0.0362   0.0393   0.8564
   4.500   0.6381   0.01130   0.00406  -0.0357   0.0333   0.8681
   4.750   0.6626   0.01159   0.00439  -0.0352   0.0284   0.8807
   5.250   0.7104   0.01213   0.00507  -0.0337   0.0227   0.9092
   5.500   0.7332   0.01243   0.00542  -0.0327   0.0205   0.9261
   5.750   0.7552   0.01291   0.00595  -0.0317   0.0184   0.9468
   6.250   0.8109   0.01374   0.00694  -0.0323   0.0167   1.0000
   6.500   0.8356   0.01426   0.00750  -0.0320   0.0158   1.0000
   6.750   0.8599   0.01481   0.00809  -0.0316   0.0152   1.0000
   7.000   0.8841   0.01534   0.00867  -0.0313   0.0145   1.0000
   7.250   0.9073   0.01598   0.00934  -0.0308   0.0137   1.0000
   7.500   0.9275   0.01707   0.01049  -0.0299   0.0130   1.0000
   7.750   0.9503   0.01777   0.01127  -0.0294   0.0128   1.0000
   8.000   0.9725   0.01856   0.01215  -0.0287   0.0126   1.0000
   8.250   0.9945   0.01941   0.01312  -0.0281   0.0123   1.0000
   8.500   1.0162   0.02028   0.01408  -0.0274   0.0119   1.0000
   8.750   1.0382   0.02106   0.01496  -0.0268   0.0113   1.0000
   9.000   1.0598   0.02182   0.01581  -0.0262   0.0109   1.0000
   9.250   1.0807   0.02263   0.01670  -0.0256   0.0105   1.0000
   9.500   1.1008   0.02355   0.01771  -0.0248   0.0102   1.0000
   9.750   1.1201   0.02447   0.01873  -0.0240   0.0099   1.0000
  10.000   1.1372   0.02571   0.02011  -0.0230   0.0095   1.0000
  10.250   1.1492   0.02794   0.02255  -0.0215   0.0092   1.0000
  10.500   1.1649   0.02919   0.02399  -0.0203   0.0090   1.0000
  10.750   1.1789   0.03052   0.02552  -0.0189   0.0087   1.0000
  11.000   1.1896   0.03212   0.02734  -0.0173   0.0084   1.0000
  11.250   1.1958   0.03374   0.02916  -0.0151   0.0081   1.0000
  11.500   1.1986   0.03548   0.03110  -0.0127   0.0078   1.0000
  11.750   1.1981   0.03754   0.03336  -0.0104   0.0076   1.0000
  12.000   1.1948   0.03990   0.03593  -0.0083   0.0075   1.0000
  12.250   1.1930   0.04208   0.03828  -0.0069   0.0073   1.0000
  12.500   1.1868   0.04494   0.04133  -0.0058   0.0072   1.0000
  12.750   1.1804   0.04796   0.04452  -0.0053   0.0071   1.0000
  13.000   1.1719   0.05146   0.04819  -0.0054   0.0070   1.0000
  13.250   1.1572   0.05612   0.05305  -0.0063   0.0070   1.0000
  13.500   1.1471   0.06047   0.05757  -0.0079   0.0069   1.0000
  13.750   1.1278   0.06673   0.06400  -0.0108   0.0069   1.0000
  14.000   1.0727   0.08079   0.07844  -0.0190   0.0070   1.0000
<< Back to NACA 64-210 (naca64210-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64-210 (naca64210-il)