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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 500,000
Max Cl/Cd: 68.52 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a210-il-500000-n5.txt
Download as CSV file: xf-naca64a210-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6156   0.09629   0.09401  -0.0154   1.0000   0.0074
 -10.750  -0.6329   0.08722   0.08500  -0.0205   1.0000   0.0075
  -9.750  -0.8164   0.03096   0.02716  -0.0447   1.0000   0.0075
  -9.500  -0.8128   0.02765   0.02339  -0.0424   1.0000   0.0077
  -9.250  -0.8065   0.02517   0.02060  -0.0400   1.0000   0.0080
  -9.000  -0.7932   0.02407   0.01937  -0.0382   1.0000   0.0082
  -8.750  -0.7644   0.02309   0.01827  -0.0394   0.9969   0.0085
  -8.500  -0.7345   0.02228   0.01733  -0.0408   0.9941   0.0089
  -8.250  -0.7059   0.02126   0.01615  -0.0418   0.9904   0.0095
  -8.000  -0.6766   0.01996   0.01461  -0.0429   0.9872   0.0102
  -7.750  -0.6481   0.01870   0.01311  -0.0436   0.9832   0.0107
  -7.500  -0.6192   0.01774   0.01196  -0.0443   0.9787   0.0110
  -7.250  -0.5914   0.01621   0.01027  -0.0451   0.9746   0.0118
  -7.000  -0.5636   0.01555   0.00954  -0.0456   0.9687   0.0123
  -6.750  -0.5334   0.01504   0.00898  -0.0464   0.9642   0.0131
  -6.500  -0.5059   0.01453   0.00838  -0.0467   0.9577   0.0139
  -6.250  -0.4779   0.01389   0.00765  -0.0470   0.9516   0.0146
  -6.000  -0.4517   0.01330   0.00696  -0.0469   0.9445   0.0151
  -5.750  -0.4250   0.01279   0.00637  -0.0468   0.9376   0.0155
  -5.500  -0.4005   0.01206   0.00556  -0.0464   0.9299   0.0165
  -5.250  -0.3747   0.01160   0.00505  -0.0461   0.9226   0.0177
  -5.000  -0.3489   0.01123   0.00462  -0.0458   0.9148   0.0187
  -4.500  -0.2967   0.01057   0.00383  -0.0453   0.8996   0.0210
  -4.250  -0.2703   0.01031   0.00348  -0.0450   0.8924   0.0221
  -4.000  -0.2442   0.00996   0.00310  -0.0447   0.8842   0.0253
  -3.750  -0.2176   0.00973   0.00284  -0.0445   0.8769   0.0297
  -3.500  -0.1910   0.00949   0.00259  -0.0443   0.8688   0.0372
  -3.250  -0.1643   0.00927   0.00237  -0.0442   0.8612   0.0492
  -3.000  -0.1377   0.00904   0.00217  -0.0440   0.8530   0.0691
  -2.750  -0.1116   0.00869   0.00197  -0.0439   0.8450   0.1149
  -2.500  -0.0872   0.00806   0.00173  -0.0436   0.8364   0.2305
  -2.250  -0.0643   0.00719   0.00149  -0.0433   0.8273   0.4110
  -2.000  -0.0393   0.00682   0.00141  -0.0429   0.8186   0.5096
  -1.750  -0.0128   0.00667   0.00136  -0.0426   0.8092   0.5553
  -1.500   0.0134   0.00652   0.00133  -0.0423   0.7998   0.6032
  -1.250   0.0392   0.00639   0.00134  -0.0418   0.7907   0.6540
  -1.000   0.0660   0.00634   0.00133  -0.0415   0.7812   0.6809
  -0.750   0.0933   0.00632   0.00130  -0.0414   0.7720   0.6957
  -0.500   0.1208   0.00633   0.00127  -0.0412   0.7628   0.7064
  -0.250   0.1485   0.00633   0.00126  -0.0412   0.7534   0.7162
   0.000   0.1760   0.00634   0.00126  -0.0411   0.7447   0.7256
   0.250   0.2036   0.00635   0.00127  -0.0411   0.7355   0.7352
   0.500   0.2312   0.00637   0.00128  -0.0410   0.7263   0.7450
   0.750   0.2587   0.00639   0.00130  -0.0409   0.7178   0.7548
   1.000   0.2862   0.00641   0.00134  -0.0409   0.7085   0.7649
   1.250   0.3137   0.00643   0.00138  -0.0408   0.6995   0.7754
   1.500   0.3409   0.00646   0.00142  -0.0406   0.6899   0.7858
   1.750   0.3678   0.00650   0.00147  -0.0404   0.6759   0.7970
   2.000   0.3942   0.00655   0.00153  -0.0401   0.6570   0.8090
   2.250   0.4197   0.00664   0.00158  -0.0396   0.6281   0.8222
   2.500   0.4441   0.00680   0.00164  -0.0388   0.5865   0.8380
   2.750   0.4682   0.00698   0.00175  -0.0380   0.5444   0.8585
   3.000   0.4920   0.00718   0.00188  -0.0372   0.4981   0.8853
   3.250   0.5164   0.00755   0.00207  -0.0365   0.4275   0.9196
   3.500   0.5433   0.00857   0.00248  -0.0371   0.2791   0.9546
   3.750   0.5721   0.00970   0.00298  -0.0383   0.1355   0.9832
   4.000   0.6021   0.01035   0.00333  -0.0394   0.0744   1.0000
   4.250   0.6255   0.01074   0.00361  -0.0387   0.0510   1.0000
   4.500   0.6497   0.01107   0.00389  -0.0382   0.0382   1.0000
   4.750   0.6739   0.01142   0.00420  -0.0377   0.0295   1.0000
   5.000   0.6985   0.01173   0.00452  -0.0372   0.0250   1.0000
   5.250   0.7224   0.01215   0.00492  -0.0366   0.0209   1.0000
   5.500   0.7469   0.01249   0.00531  -0.0361   0.0194   1.0000
   5.750   0.7710   0.01288   0.00575  -0.0355   0.0180   1.0000
   6.000   0.7947   0.01331   0.00621  -0.0350   0.0168   1.0000
   6.250   0.8178   0.01384   0.00676  -0.0343   0.0157   1.0000
   6.500   0.8394   0.01453   0.00750  -0.0334   0.0147   1.0000
   6.750   0.8624   0.01505   0.00808  -0.0327   0.0143   1.0000
   7.000   0.8848   0.01564   0.00875  -0.0319   0.0140   1.0000
   7.250   0.9068   0.01627   0.00946  -0.0311   0.0136   1.0000
   7.500   0.9285   0.01696   0.01022  -0.0303   0.0132   1.0000
   7.750   0.9499   0.01769   0.01103  -0.0294   0.0128   1.0000
   8.000   0.9716   0.01837   0.01177  -0.0286   0.0123   1.0000
   8.250   0.9935   0.01898   0.01246  -0.0279   0.0117   1.0000
   8.500   1.0149   0.01965   0.01317  -0.0272   0.0113   1.0000
   8.750   1.0347   0.02056   0.01415  -0.0262   0.0109   1.0000
   9.000   1.0514   0.02209   0.01581  -0.0249   0.0104   1.0000
   9.250   1.0702   0.02328   0.01715  -0.0238   0.0101   1.0000
   9.500   1.0897   0.02427   0.01828  -0.0228   0.0099   1.0000
   9.750   1.1085   0.02528   0.01945  -0.0218   0.0095   1.0000
  10.000   1.1264   0.02634   0.02068  -0.0207   0.0091   1.0000
  10.250   1.1433   0.02744   0.02193  -0.0195   0.0087   1.0000
  10.500   1.1587   0.02863   0.02327  -0.0182   0.0084   1.0000
  10.750   1.1727   0.02984   0.02463  -0.0167   0.0081   1.0000
  11.000   1.1845   0.03099   0.02590  -0.0150   0.0079   1.0000
  11.250   1.1941   0.03218   0.02721  -0.0131   0.0077   1.0000
  11.500   1.2015   0.03352   0.02868  -0.0110   0.0075   1.0000
  11.750   1.2055   0.03518   0.03049  -0.0089   0.0073   1.0000
  12.000   1.2021   0.03771   0.03323  -0.0065   0.0072   1.0000
  12.250   1.1935   0.04089   0.03668  -0.0042   0.0070   1.0000
  12.500   1.1885   0.04371   0.03975  -0.0027   0.0069   1.0000
  12.750   1.1801   0.04707   0.04335  -0.0016   0.0068   1.0000
  13.000   1.1679   0.05109   0.04763  -0.0012   0.0068   1.0000
  13.250   1.1518   0.05594   0.05272  -0.0017   0.0067   1.0000
  13.500   1.1311   0.06191   0.05894  -0.0034   0.0066   1.0000
  13.750   1.1076   0.06895   0.06619  -0.0065   0.0066   1.0000
  14.000   1.0811   0.07747   0.07492  -0.0113   0.0067   1.0000
  14.250   1.0508   0.08811   0.08575  -0.0181   0.0068   1.0000
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