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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 500,000
Max Cl/Cd: 84.98 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a210-il-500000.txt
Download as CSV file: xf-naca64a210-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5604   0.08453   0.08230  -0.0291   1.0000   0.0209
  -9.500  -0.5680   0.07547   0.07320  -0.0379   1.0000   0.0209
  -9.250  -0.5814   0.06925   0.06691  -0.0438   1.0000   0.0209
  -9.000  -0.5962   0.06477   0.06232  -0.0459   1.0000   0.0209
  -8.750  -0.6051   0.06032   0.05771  -0.0468   1.0000   0.0209
  -8.500  -0.6112   0.05619   0.05339  -0.0466   1.0000   0.0210
  -8.250  -0.6404   0.04763   0.04463  -0.0450   1.0000   0.0217
  -8.000  -0.6396   0.04523   0.04217  -0.0428   1.0000   0.0221
  -7.750  -0.6390   0.04342   0.04031  -0.0399   1.0000   0.0225
  -7.500  -0.6393   0.04169   0.03849  -0.0366   1.0000   0.0229
  -7.250  -0.6182   0.03885   0.03547  -0.0380   0.9977   0.0239
  -7.000  -0.5906   0.03534   0.03164  -0.0401   0.9949   0.0258
  -6.750  -0.5706   0.02577   0.02103  -0.0397   0.9903   0.0199
  -6.500  -0.5426   0.02172   0.01646  -0.0405   0.9872   0.0194
  -6.250  -0.5101   0.01934   0.01375  -0.0418   0.9850   0.0197
  -6.000  -0.4756   0.01773   0.01190  -0.0435   0.9834   0.0203
  -5.750  -0.4450   0.01642   0.01039  -0.0442   0.9796   0.0214
  -5.500  -0.4143   0.01451   0.00837  -0.0453   0.9765   0.0226
  -5.250  -0.3806   0.01358   0.00739  -0.0468   0.9738   0.0237
  -5.000  -0.3464   0.01281   0.00658  -0.0483   0.9712   0.0251
  -4.750  -0.3165   0.01218   0.00590  -0.0489   0.9664   0.0267
  -4.500  -0.2862   0.01179   0.00545  -0.0495   0.9609   0.0284
  -4.250  -0.2574   0.01081   0.00440  -0.0499   0.9563   0.0313
  -4.000  -0.2316   0.01038   0.00395  -0.0495   0.9486   0.0347
  -3.750  -0.2035   0.01003   0.00354  -0.0495   0.9427   0.0392
  -3.500  -0.1785   0.00955   0.00307  -0.0490   0.9349   0.0540
  -3.250  -0.1539   0.00888   0.00268  -0.0485   0.9279   0.1220
  -3.000  -0.1338   0.00771   0.00230  -0.0477   0.9190   0.3313
  -2.750  -0.1123   0.00690   0.00214  -0.0467   0.9118   0.5208
  -2.500  -0.0877   0.00667   0.00208  -0.0460   0.9030   0.5846
  -2.250  -0.0618   0.00654   0.00202  -0.0454   0.8958   0.6256
  -2.000  -0.0358   0.00645   0.00197  -0.0449   0.8872   0.6546
  -1.750  -0.0093   0.00640   0.00193  -0.0445   0.8793   0.6784
  -1.500   0.0168   0.00635   0.00190  -0.0439   0.8711   0.7048
  -1.250   0.0424   0.00632   0.00193  -0.0433   0.8623   0.7358
  -0.750   0.0957   0.00626   0.00187  -0.0424   0.8450   0.7683
  -0.500   0.1228   0.00624   0.00183  -0.0422   0.8365   0.7804
  -0.250   0.1498   0.00619   0.00179  -0.0419   0.8274   0.7913
   0.000   0.1768   0.00615   0.00177  -0.0417   0.8177   0.8027
   0.250   0.2038   0.00612   0.00174  -0.0414   0.8089   0.8146
   0.500   0.2306   0.00609   0.00173  -0.0411   0.7993   0.8277
   0.750   0.2573   0.00605   0.00174  -0.0408   0.7894   0.8420
   1.000   0.2839   0.00603   0.00175  -0.0404   0.7802   0.8579
   1.250   0.3102   0.00602   0.00178  -0.0400   0.7704   0.8768
   1.500   0.3366   0.00600   0.00183  -0.0395   0.7599   0.8992
   1.750   0.3643   0.00602   0.00188  -0.0392   0.7477   0.9248
   2.000   0.3967   0.00606   0.00193  -0.0401   0.7327   0.9483
   2.250   0.4314   0.00613   0.00194  -0.0414   0.7110   0.9688
   2.500   0.4680   0.00622   0.00195  -0.0433   0.6814   0.9839
   2.750   0.5064   0.00634   0.00200  -0.0457   0.6548   0.9949
   3.000   0.5398   0.00645   0.00206  -0.0471   0.6293   1.0000
   3.250   0.5632   0.00663   0.00214  -0.0463   0.5983   1.0000
   3.500   0.5855   0.00689   0.00223  -0.0453   0.5524   1.0000
   3.750   0.6066   0.00728   0.00239  -0.0441   0.4871   1.0000
   4.000   0.6205   0.00839   0.00276  -0.0418   0.3254   1.0000
   4.250   0.6341   0.00975   0.00334  -0.0399   0.1601   1.0000
   4.500   0.6524   0.01071   0.00385  -0.0385   0.0715   1.0000
   4.750   0.6744   0.01133   0.00434  -0.0376   0.0439   1.0000
   5.000   0.6970   0.01190   0.00490  -0.0367   0.0344   1.0000
   5.250   0.7194   0.01251   0.00550  -0.0358   0.0293   1.0000
   5.500   0.7416   0.01313   0.00619  -0.0348   0.0267   1.0000
   5.750   0.7645   0.01368   0.00678  -0.0340   0.0250   1.0000
   6.000   0.7869   0.01429   0.00745  -0.0331   0.0235   1.0000
   6.250   0.8086   0.01499   0.00817  -0.0322   0.0223   1.0000
   6.500   0.8284   0.01603   0.00926  -0.0309   0.0212   1.0000
   6.750   0.8453   0.01804   0.01136  -0.0292   0.0202   1.0000
   7.000   0.8696   0.01849   0.01190  -0.0287   0.0196   1.0000
   7.250   0.8926   0.01938   0.01289  -0.0279   0.0189   1.0000
   7.500   0.9154   0.02061   0.01422  -0.0271   0.0184   1.0000
   7.750   0.9380   0.02201   0.01576  -0.0263   0.0179   1.0000
   8.000   0.9602   0.02364   0.01755  -0.0255   0.0175   1.0000
   8.250   0.9813   0.02554   0.01967  -0.0245   0.0171   1.0000
   8.500   1.0018   0.02693   0.02121  -0.0236   0.0165   1.0000
   8.750   1.0213   0.02791   0.02226  -0.0228   0.0157   1.0000
   9.000   1.0374   0.03023   0.02475  -0.0216   0.0152   1.0000
   9.250   1.0495   0.03349   0.02833  -0.0198   0.0150   1.0000
   9.500   1.0591   0.03665   0.03183  -0.0177   0.0151   1.0000
  12.250   0.6572   0.11474   0.11266  -0.0159   0.0255   1.0000
  12.500   0.6463   0.12072   0.11863  -0.0184   0.0249   1.0000
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