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NACA 66-210 (naca66210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-210 (naca66210-il)
Reynolds number: 200,000
Max Cl/Cd: 46.65 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66210-il-200000-n5.txt
Download as CSV file: xf-naca66210-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5195   0.08602   0.08244  -0.0421   1.0000   0.0150
  -9.750  -0.5290   0.07952   0.07599  -0.0466   1.0000   0.0147
  -9.500  -0.5539   0.07029   0.06679  -0.0536   1.0000   0.0141
  -9.250  -0.5879   0.06298   0.05937  -0.0544   1.0000   0.0134
  -9.000  -0.6100   0.06032   0.05667  -0.0506   1.0000   0.0134
  -8.750  -0.6235   0.05704   0.05328  -0.0485   0.9963   0.0134
  -8.500  -0.6190   0.05113   0.04705  -0.0507   0.9869   0.0134
  -8.250  -0.6088   0.04694   0.04259  -0.0524   0.9798   0.0137
  -8.000  -0.5859   0.04607   0.04162  -0.0543   0.9760   0.0149
  -7.750  -0.5707   0.04270   0.03795  -0.0549   0.9692   0.0160
  -7.500  -0.5534   0.03824   0.03306  -0.0555   0.9644   0.0166
  -7.250  -0.5385   0.03423   0.02857  -0.0548   0.9573   0.0169
  -7.000  -0.5178   0.03052   0.02433  -0.0546   0.9526   0.0174
  -6.750  -0.4970   0.02770   0.02102  -0.0538   0.9471   0.0182
  -6.500  -0.4726   0.02617   0.01905  -0.0534   0.9420   0.0194
  -6.250  -0.4485   0.02377   0.01644  -0.0538   0.9384   0.0209
  -6.000  -0.4240   0.02232   0.01475  -0.0535   0.9340   0.0217
  -5.750  -0.3989   0.02104   0.01327  -0.0532   0.9295   0.0226
  -5.500  -0.3719   0.01986   0.01191  -0.0532   0.9260   0.0237
  -5.250  -0.3440   0.01902   0.01093  -0.0534   0.9232   0.0258
  -5.000  -0.3201   0.01823   0.01002  -0.0527   0.9180   0.0271
  -4.750  -0.2946   0.01737   0.00903  -0.0523   0.9139   0.0279
  -4.500  -0.2689   0.01657   0.00816  -0.0521   0.9105   0.0287
  -4.250  -0.2477   0.01548   0.00705  -0.0511   0.9064   0.0308
  -4.000  -0.2253   0.01491   0.00646  -0.0504   0.9018   0.0332
  -3.750  -0.2008   0.01447   0.00598  -0.0500   0.8983   0.0368
  -3.500  -0.1754   0.01407   0.00546  -0.0497   0.8954   0.0399
  -3.250  -0.1523   0.01367   0.00500  -0.0490   0.8911   0.0435
  -3.000  -0.1281   0.01334   0.00465  -0.0485   0.8870   0.0515
  -2.750  -0.1034   0.01292   0.00432  -0.0481   0.8837   0.0736
  -2.500  -0.0874   0.01142   0.00386  -0.0470   0.8807   0.3374
  -2.250  -0.0798   0.01017   0.00406  -0.0432   0.8755   0.6806
  -2.000  -0.0596   0.01037   0.00449  -0.0407   0.8721   0.7721
  -1.750  -0.0363   0.01059   0.00472  -0.0391   0.8692   0.8043
  -1.500  -0.0109   0.01073   0.00479  -0.0381   0.8669   0.8206
  -1.250   0.0120   0.01091   0.00496  -0.0368   0.8633   0.8348
  -1.000   0.0349   0.01109   0.00513  -0.0354   0.8600   0.8476
  -0.750   0.0609   0.01112   0.00512  -0.0351   0.8571   0.8544
  -0.500   0.0884   0.01112   0.00507  -0.0350   0.8547   0.8574
  -0.250   0.1166   0.01110   0.00501  -0.0352   0.8526   0.8604
   0.000   0.1422   0.01114   0.00505  -0.0351   0.8491   0.8640
   0.250   0.1684   0.01117   0.00507  -0.0351   0.8457   0.8678
   0.500   0.1953   0.01119   0.00510  -0.0350   0.8427   0.8704
   0.750   0.2232   0.01118   0.00510  -0.0351   0.8401   0.8731
   1.000   0.2505   0.01117   0.00511  -0.0351   0.8366   0.8763
   1.250   0.2756   0.01120   0.00518  -0.0347   0.8311   0.8805
   1.500   0.3028   0.01119   0.00521  -0.0346   0.8273   0.8835
   1.750   0.3313   0.01116   0.00522  -0.0347   0.8242   0.8862
   2.000   0.3555   0.01113   0.00526  -0.0340   0.8158   0.8899
   2.250   0.3819   0.01089   0.00506  -0.0333   0.8028   0.8936
   2.500   0.4078   0.01060   0.00478  -0.0323   0.7843   0.8970
   2.750   0.4326   0.01040   0.00461  -0.0312   0.7638   0.9005
   3.000   0.4561   0.01020   0.00439  -0.0297   0.7284   0.9048
   3.250   0.4749   0.01018   0.00394  -0.0271   0.5978   0.9098
   3.500   0.4728   0.01166   0.00418  -0.0214   0.3548   0.9164
   4.000   0.4928   0.01406   0.00521  -0.0161   0.0626   0.9305
   4.250   0.5137   0.01455   0.00564  -0.0150   0.0470   0.9374
   4.500   0.5369   0.01497   0.00613  -0.0144   0.0401   0.9432
   4.750   0.5581   0.01559   0.00681  -0.0134   0.0358   0.9505
   5.000   0.5836   0.01603   0.00736  -0.0133   0.0326   0.9565
   5.250   0.6087   0.01660   0.00799  -0.0133   0.0294   0.9637
   5.500   0.6355   0.01738   0.00883  -0.0137   0.0273   0.9704
   5.750   0.6616   0.01855   0.01005  -0.0141   0.0255   0.9783
   6.000   0.6897   0.02002   0.01158  -0.0147   0.0243   0.9864
   6.250   0.7203   0.02113   0.01280  -0.0157   0.0237   0.9989
   6.500   0.7441   0.02224   0.01402  -0.0152   0.0230   1.0000
   6.750   0.7680   0.02326   0.01520  -0.0148   0.0218   1.0000
   7.000   0.7920   0.02437   0.01645  -0.0145   0.0205   1.0000
   7.250   0.8166   0.02589   0.01816  -0.0142   0.0198   1.0000
   7.500   0.8399   0.02752   0.02000  -0.0137   0.0191   1.0000
   7.750   0.8616   0.02932   0.02204  -0.0131   0.0185   1.0000
   8.000   0.8812   0.03109   0.02403  -0.0122   0.0178   1.0000
   8.250   0.8985   0.03299   0.02610  -0.0114   0.0170   1.0000
   8.500   0.9109   0.03575   0.02925  -0.0097   0.0160   1.0000
   8.750   0.9219   0.03861   0.03256  -0.0076   0.0155   1.0000
   9.000   0.9281   0.04204   0.03643  -0.0051   0.0151   1.0000
   9.250   0.9295   0.04578   0.04058  -0.0023   0.0149   1.0000
   9.500   0.9260   0.04971   0.04488   0.0008   0.0147   1.0000
   9.750   0.9175   0.05367   0.04916   0.0040   0.0145   1.0000
  10.000   0.9039   0.05719   0.05291   0.0075   0.0143   1.0000
  10.250   0.8878   0.06080   0.05673   0.0104   0.0141   1.0000
  10.500   0.8690   0.06482   0.06093   0.0123   0.0141   1.0000
  10.750   0.8489   0.06931   0.06559   0.0129   0.0142   1.0000
  11.000   0.8276   0.07445   0.07087   0.0121   0.0145   1.0000
  11.250   0.8057   0.08079   0.07734   0.0093   0.0143   1.0000
  11.500   0.7836   0.08878   0.08541   0.0042   0.0147   1.0000
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