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NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 82.6 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65210-il-1000000.txt
Download as CSV file: xf-naca65210-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6529   0.05116   0.04922  -0.0470   1.0000   0.0090
  -8.750  -0.6672   0.04593   0.04379  -0.0452   1.0000   0.0089
  -8.500  -0.6822   0.04050   0.03812  -0.0422   1.0000   0.0086
  -8.250  -0.6926   0.02584   0.02239  -0.0420   0.9901   0.0089
  -8.000  -0.6728   0.01958   0.01534  -0.0430   0.9846   0.0096
  -7.750  -0.6428   0.01853   0.01418  -0.0444   0.9795   0.0101
  -7.500  -0.6122   0.01768   0.01321  -0.0456   0.9735   0.0105
  -7.250  -0.5823   0.01693   0.01235  -0.0466   0.9665   0.0111
  -7.000  -0.5556   0.01581   0.01107  -0.0468   0.9575   0.0117
  -6.750  -0.5309   0.01496   0.01008  -0.0463   0.9475   0.0123
  -6.500  -0.5060   0.01441   0.00941  -0.0459   0.9381   0.0129
  -6.250  -0.4840   0.01309   0.00791  -0.0450   0.9283   0.0137
  -6.000  -0.4607   0.01229   0.00705  -0.0444   0.9187   0.0145
  -5.750  -0.4358   0.01191   0.00661  -0.0440   0.9102   0.0152
  -5.500  -0.4109   0.01146   0.00609  -0.0435   0.9016   0.0159
  -5.250  -0.3857   0.01100   0.00557  -0.0431   0.8933   0.0168
  -5.000  -0.3603   0.01064   0.00513  -0.0428   0.8853   0.0177
  -4.750  -0.3332   0.01055   0.00500  -0.0427   0.8771   0.0184
  -4.500  -0.3104   0.00959   0.00390  -0.0420   0.8694   0.0197
  -4.250  -0.2848   0.00913   0.00340  -0.0417   0.8615   0.0211
  -4.000  -0.2583   0.00886   0.00308  -0.0416   0.8545   0.0226
  -3.750  -0.2314   0.00863   0.00281  -0.0415   0.8468   0.0243
  -3.500  -0.2042   0.00849   0.00262  -0.0414   0.8398   0.0257
  -3.250  -0.1776   0.00812   0.00217  -0.0413   0.8323   0.0290
  -3.000  -0.1504   0.00791   0.00193  -0.0413   0.8257   0.0334
  -2.750  -0.1228   0.00776   0.00174  -0.0413   0.8185   0.0372
  -2.500  -0.0962   0.00740   0.00151  -0.0413   0.8119   0.0807
  -2.250  -0.0728   0.00615   0.00117  -0.0414   0.8045   0.3451
  -2.000  -0.0485   0.00529   0.00099  -0.0413   0.7981   0.5547
  -1.750  -0.0209   0.00512   0.00096  -0.0414   0.7913   0.6089
  -1.500   0.0067   0.00505   0.00094  -0.0414   0.7849   0.6448
  -1.250   0.0346   0.00498   0.00094  -0.0414   0.7783   0.6750
  -1.000   0.0622   0.00495   0.00097  -0.0414   0.7720   0.7040
  -0.750   0.0903   0.00494   0.00098  -0.0415   0.7657   0.7191
  -0.500   0.1184   0.00495   0.00098  -0.0415   0.7592   0.7320
  -0.250   0.1466   0.00497   0.00099  -0.0416   0.7533   0.7421
   0.000   0.1750   0.00496   0.00099  -0.0418   0.7468   0.7483
   0.250   0.2032   0.00499   0.00100  -0.0419   0.7409   0.7551
   0.500   0.2317   0.00498   0.00102  -0.0421   0.7346   0.7615
   0.750   0.2598   0.00501   0.00104  -0.0421   0.7279   0.7682
   1.000   0.2881   0.00502   0.00106  -0.0423   0.7194   0.7749
   1.250   0.3158   0.00504   0.00108  -0.0423   0.7058   0.7816
   1.500   0.3435   0.00509   0.00109  -0.0422   0.6900   0.7886
   1.750   0.3708   0.00513   0.00112  -0.0421   0.6727   0.7954
   2.000   0.3981   0.00521   0.00116  -0.0421   0.6484   0.8026
   2.250   0.4249   0.00531   0.00121  -0.0419   0.6198   0.8095
   2.500   0.4516   0.00547   0.00128  -0.0417   0.5861   0.8171
   2.750   0.4766   0.00577   0.00139  -0.0413   0.5221   0.8244
   3.000   0.4956   0.00684   0.00175  -0.0401   0.3433   0.8324
   3.250   0.5135   0.00810   0.00225  -0.0389   0.1494   0.8406
   3.500   0.5349   0.00893   0.00264  -0.0381   0.0447   0.8487
   3.750   0.5607   0.00922   0.00290  -0.0378   0.0336   0.8573
   4.000   0.5863   0.00946   0.00320  -0.0374   0.0288   0.8654
   4.250   0.6122   0.00970   0.00348  -0.0372   0.0257   0.8742
   4.500   0.6356   0.01018   0.00405  -0.0364   0.0218   0.8831
   4.750   0.6606   0.01044   0.00436  -0.0359   0.0206   0.8922
   5.250   0.7091   0.01101   0.00505  -0.0346   0.0182   0.9126
   5.500   0.7320   0.01135   0.00544  -0.0338   0.0172   0.9234
   5.750   0.7533   0.01180   0.00595  -0.0326   0.0163   0.9354
   6.000   0.7696   0.01269   0.00696  -0.0305   0.0154   0.9516
   6.250   0.7902   0.01356   0.00794  -0.0293   0.0149   0.9731
   6.500   0.8221   0.01382   0.00825  -0.0305   0.0143   1.0000
   6.750   0.8468   0.01441   0.00888  -0.0302   0.0137   1.0000
   7.000   0.8709   0.01509   0.00961  -0.0298   0.0131   1.0000
   7.250   0.8948   0.01580   0.01038  -0.0294   0.0126   1.0000
   7.500   0.9185   0.01653   0.01115  -0.0290   0.0122   1.0000
   7.750   0.9423   0.01716   0.01183  -0.0287   0.0117   1.0000
   8.000   0.9651   0.01799   0.01271  -0.0282   0.0113   1.0000
   8.250   0.9831   0.02078   0.01573  -0.0271   0.0104   1.0000
   8.500   1.0066   0.02126   0.01631  -0.0266   0.0101   1.0000
   8.750   1.0284   0.02229   0.01748  -0.0260   0.0098   1.0000
   9.000   1.0482   0.02389   0.01927  -0.0250   0.0093   1.0000
   9.250   1.0672   0.02535   0.02091  -0.0240   0.0089   1.0000
   9.500   1.0853   0.02666   0.02237  -0.0230   0.0086   1.0000
   9.750   1.1014   0.02816   0.02404  -0.0218   0.0083   1.0000
  10.000   1.1178   0.02920   0.02520  -0.0207   0.0081   1.0000
  10.250   1.1327   0.03030   0.02641  -0.0194   0.0079   1.0000
  10.500   1.1466   0.03124   0.02744  -0.0181   0.0077   1.0000
  10.750   1.1228   0.03727   0.03400  -0.0131   0.0072   1.0000
  11.000   1.1008   0.04114   0.03822  -0.0078   0.0071   1.0000
  11.250   1.0880   0.04409   0.04140  -0.0045   0.0070   1.0000
  11.500   1.0743   0.04732   0.04483  -0.0020   0.0070   1.0000
  11.750   1.0382   0.05359   0.05140  -0.0001   0.0069   1.0000
  12.000   0.9940   0.06167   0.05974  -0.0008   0.0070   1.0000
  12.250   0.9643   0.06868   0.06691  -0.0036   0.0070   1.0000
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