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NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 500,000
Max Cl/Cd: 72.94 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65210-il-500000.txt
Download as CSV file: xf-naca65210-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5299   0.09138   0.08908  -0.0312   1.0000   0.0185
 -10.000  -0.5324   0.08480   0.08252  -0.0359   1.0000   0.0185
  -9.750  -0.5417   0.07705   0.07473  -0.0426   1.0000   0.0185
  -6.750  -0.5414   0.02522   0.02030  -0.0449   0.9826   0.0193
  -6.500  -0.5129   0.02228   0.01700  -0.0457   0.9772   0.0192
  -6.250  -0.4812   0.02139   0.01616  -0.0477   0.9731   0.0212
  -6.000  -0.4485   0.01871   0.01313  -0.0489   0.9697   0.0213
  -5.750  -0.4204   0.01717   0.01139  -0.0490   0.9621   0.0220
  -5.500  -0.3896   0.01583   0.00989  -0.0497   0.9567   0.0228
  -5.250  -0.3630   0.01497   0.00892  -0.0494   0.9482   0.0241
  -5.000  -0.3355   0.01439   0.00824  -0.0493   0.9410   0.0254
  -4.750  -0.3106   0.01390   0.00766  -0.0487   0.9317   0.0260
  -4.500  -0.2893   0.01225   0.00591  -0.0475   0.9233   0.0273
  -4.250  -0.2666   0.01145   0.00506  -0.0466   0.9148   0.0291
  -4.000  -0.2421   0.01103   0.00462  -0.0461   0.9062   0.0316
  -3.500  -0.1917   0.01029   0.00373  -0.0451   0.8903   0.0359
  -3.250  -0.1669   0.00974   0.00309  -0.0446   0.8834   0.0408
  -3.000  -0.1407   0.00946   0.00278  -0.0443   0.8754   0.0476
  -2.750  -0.1157   0.00886   0.00239  -0.0440   0.8684   0.1076
  -2.500  -0.0987   0.00675   0.00192  -0.0435   0.8600   0.5509
  -2.250  -0.0732   0.00652   0.00191  -0.0430   0.8534   0.6358
  -2.000  -0.0463   0.00647   0.00189  -0.0427   0.8462   0.6719
  -1.750  -0.0199   0.00645   0.00193  -0.0423   0.8400   0.7056
  -1.500   0.0063   0.00647   0.00200  -0.0417   0.8326   0.7371
  -1.250   0.0333   0.00652   0.00203  -0.0414   0.8268   0.7552
  -1.000   0.0604   0.00653   0.00206  -0.0411   0.8196   0.7686
  -0.750   0.0878   0.00655   0.00205  -0.0409   0.8137   0.7784
  -0.500   0.1158   0.00655   0.00203  -0.0410   0.8068   0.7856
  -0.250   0.1436   0.00655   0.00202  -0.0410   0.8007   0.7917
   0.000   0.1715   0.00657   0.00202  -0.0410   0.7944   0.7987
   0.250   0.1993   0.00657   0.00203  -0.0410   0.7880   0.8051
   0.500   0.2271   0.00660   0.00205  -0.0410   0.7822   0.8120
   0.750   0.2549   0.00660   0.00208  -0.0411   0.7756   0.8188
   1.000   0.2826   0.00664   0.00211  -0.0410   0.7701   0.8257
   1.250   0.3103   0.00665   0.00217  -0.0410   0.7632   0.8328
   1.500   0.3377   0.00668   0.00221  -0.0409   0.7565   0.8398
   1.750   0.3644   0.00666   0.00221  -0.0405   0.7437   0.8472
   2.000   0.3904   0.00666   0.00219  -0.0400   0.7276   0.8547
   2.250   0.4165   0.00665   0.00221  -0.0395   0.7096   0.8622
   2.500   0.4415   0.00668   0.00219  -0.0387   0.6813   0.8701
   2.750   0.4666   0.00674   0.00222  -0.0380   0.6549   0.8779
   3.000   0.4919   0.00684   0.00228  -0.0374   0.6251   0.8868
   3.250   0.5142   0.00705   0.00237  -0.0362   0.5671   0.8949
   3.500   0.5272   0.00823   0.00270  -0.0337   0.3637   0.9053
   3.750   0.5348   0.01022   0.00347  -0.0309   0.0876   0.9176
   4.000   0.5542   0.01084   0.00391  -0.0294   0.0455   0.9294
   4.250   0.5746   0.01118   0.00431  -0.0278   0.0381   0.9419
   4.500   0.5954   0.01152   0.00471  -0.0264   0.0336   0.9563
   4.750   0.6191   0.01233   0.00561  -0.0258   0.0298   0.9720
   5.000   0.6527   0.01287   0.00621  -0.0274   0.0282   0.9868
   5.250   0.6813   0.01346   0.00683  -0.0280   0.0261   1.0000
   5.500   0.7058   0.01405   0.00745  -0.0278   0.0243   1.0000
   5.750   0.7289   0.01489   0.00831  -0.0274   0.0231   1.0000
   6.000   0.7500   0.01635   0.00980  -0.0265   0.0220   1.0000
   6.250   0.7734   0.01856   0.01209  -0.0260   0.0213   1.0000
   6.500   0.7993   0.01929   0.01294  -0.0258   0.0208   1.0000
   6.750   0.8248   0.02010   0.01386  -0.0255   0.0199   1.0000
   7.000   0.8500   0.02139   0.01529  -0.0251   0.0191   1.0000
   7.250   0.8744   0.02317   0.01726  -0.0246   0.0186   1.0000
   7.500   0.8973   0.02545   0.01980  -0.0238   0.0184   1.0000
   7.750   0.9169   0.02886   0.02359  -0.0225   0.0186   1.0000
   8.000   0.9327   0.03235   0.02748  -0.0207   0.0188   1.0000
   8.250   0.9373   0.03826   0.03385  -0.0182   0.0204   1.0000
  11.750   0.6794   0.10742   0.10550  -0.0197   0.0213   1.0000
  12.000   0.6678   0.11667   0.11476  -0.0251   0.0213   1.0000
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