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NACA 66 (p51htip-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 66 (p51htip-il)
Reynolds number: 200,000
Max Cl/Cd: 47.99 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51htip-il-200000-n5.txt
Download as CSV file: xf-p51htip-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5289   0.06967   0.06610  -0.0680   0.9694   0.0181
 -10.250  -0.5448   0.06289   0.05914  -0.0733   0.9529   0.0179
 -10.000  -0.5625   0.05803   0.05408  -0.0744   0.9376   0.0178
  -9.750  -0.5795   0.05445   0.05029  -0.0726   0.9246   0.0177
  -9.500  -0.5953   0.05127   0.04689  -0.0693   0.9144   0.0175
  -9.250  -0.6061   0.04761   0.04294  -0.0664   0.9060   0.0175
  -9.000  -0.6117   0.04404   0.03903  -0.0636   0.8993   0.0177
  -8.750  -0.6126   0.04063   0.03525  -0.0608   0.8931   0.0178
  -8.500  -0.6098   0.03742   0.03164  -0.0580   0.8884   0.0180
  -8.250  -0.6022   0.03435   0.02813  -0.0558   0.8830   0.0184
  -8.000  -0.5908   0.03177   0.02504  -0.0536   0.8783   0.0193
  -7.750  -0.5764   0.02973   0.02255  -0.0517   0.8748   0.0199
  -7.500  -0.5582   0.02773   0.02033  -0.0509   0.8716   0.0204
  -7.250  -0.5374   0.02623   0.01864  -0.0502   0.8680   0.0209
  -7.000  -0.5154   0.02490   0.01711  -0.0496   0.8649   0.0215
  -6.750  -0.4924   0.02367   0.01568  -0.0490   0.8622   0.0222
  -6.500  -0.4685   0.02251   0.01434  -0.0485   0.8599   0.0232
  -6.250  -0.4437   0.02149   0.01315  -0.0481   0.8576   0.0243
  -6.000  -0.4186   0.02083   0.01233  -0.0478   0.8546   0.0258
  -5.750  -0.3941   0.01961   0.01105  -0.0476   0.8519   0.0274
  -5.500  -0.3706   0.01876   0.01018  -0.0471   0.8492   0.0287
  -5.250  -0.3473   0.01810   0.00946  -0.0465   0.8468   0.0302
  -5.000  -0.3239   0.01759   0.00889  -0.0459   0.8447   0.0326
  -4.750  -0.3006   0.01705   0.00829  -0.0453   0.8425   0.0342
  -4.500  -0.2775   0.01658   0.00776  -0.0447   0.8398   0.0355
  -4.250  -0.2571   0.01589   0.00705  -0.0437   0.8371   0.0378
  -4.000  -0.2343   0.01549   0.00663  -0.0431   0.8348   0.0414
  -3.750  -0.2106   0.01517   0.00624  -0.0426   0.8328   0.0452
  -3.500  -0.1870   0.01483   0.00584  -0.0419   0.8310   0.0495
  -3.250  -0.1633   0.01450   0.00548  -0.0413   0.8293   0.0586
  -3.000  -0.1424   0.01397   0.00522  -0.0405   0.8265   0.1082
  -2.750  -0.1303   0.01276   0.00490  -0.0386   0.8236   0.3183
  -2.500  -0.1244   0.01143   0.00477  -0.0349   0.8208   0.5820
  -2.250  -0.1059   0.01142   0.00526  -0.0322   0.8189   0.7393
  -2.000  -0.0832   0.01173   0.00566  -0.0304   0.8172   0.7873
  -1.750  -0.0595   0.01202   0.00594  -0.0288   0.8157   0.8133
  -1.500  -0.0344   0.01232   0.00621  -0.0275   0.8143   0.8307
  -1.250  -0.0106   0.01248   0.00633  -0.0268   0.8119   0.8410
  -1.000   0.0160   0.01260   0.00642  -0.0266   0.8097   0.8450
  -0.750   0.0423   0.01267   0.00647  -0.0265   0.8075   0.8492
  -0.500   0.0681   0.01269   0.00644  -0.0263   0.8054   0.8537
  -0.250   0.0945   0.01269   0.00640  -0.0263   0.8035   0.8573
   0.000   0.1223   0.01272   0.00640  -0.0265   0.8020   0.8596
   0.250   0.1501   0.01272   0.00639  -0.0266   0.8005   0.8622
   0.500   0.1770   0.01275   0.00641  -0.0266   0.7987   0.8653
   0.750   0.2005   0.01287   0.00655  -0.0263   0.7950   0.8694
   1.000   0.2260   0.01293   0.00663  -0.0261   0.7921   0.8725
   1.250   0.2532   0.01296   0.00669  -0.0261   0.7896   0.8748
   1.500   0.2809   0.01296   0.00671  -0.0262   0.7875   0.8775
   1.750   0.3091   0.01294   0.00671  -0.0263   0.7855   0.8808
   2.000   0.3326   0.01303   0.00687  -0.0259   0.7814   0.8851
   2.250   0.3576   0.01310   0.00700  -0.0255   0.7771   0.8881
   2.500   0.3855   0.01306   0.00702  -0.0255   0.7737   0.8907
   2.750   0.4151   0.01293   0.00695  -0.0258   0.7708   0.8934
   3.000   0.4376   0.01297   0.00708  -0.0249   0.7636   0.8978
   3.250   0.4660   0.01248   0.00661  -0.0244   0.7520   0.9016
   3.500   0.4921   0.01195   0.00613  -0.0232   0.7316   0.9045
   3.750   0.5164   0.01150   0.00568  -0.0218   0.7017   0.9082
   4.000   0.5365   0.01118   0.00526  -0.0197   0.6328   0.9133
   4.250   0.5405   0.01187   0.00491  -0.0147   0.4460   0.9194
   4.500   0.5399   0.01305   0.00543  -0.0100   0.3101   0.9281
   4.750   0.5434   0.01427   0.00603  -0.0064   0.1795   0.9363
   5.000   0.5507   0.01540   0.00665  -0.0035   0.0777   0.9459
   5.500   0.5931   0.01661   0.00775  -0.0023   0.0435   0.9598
   5.750   0.6176   0.01731   0.00847  -0.0024   0.0387   0.9660
   6.000   0.6429   0.01784   0.00910  -0.0027   0.0352   0.9733
   6.250   0.6700   0.01852   0.00984  -0.0035   0.0323   0.9797
   6.500   0.6950   0.01937   0.01073  -0.0040   0.0303   0.9876
   6.750   0.7181   0.02057   0.01197  -0.0043   0.0286   0.9982
   7.000   0.7289   0.02107   0.01252  -0.0018   0.0277   1.0000
   7.250   0.7427   0.02163   0.01313   0.0002   0.0263   1.0000
   7.500   0.7593   0.02234   0.01388   0.0016   0.0250   1.0000
   7.750   0.7780   0.02319   0.01477   0.0027   0.0239   1.0000
   8.000   0.7984   0.02411   0.01574   0.0034   0.0231   1.0000
   8.250   0.8209   0.02519   0.01684   0.0039   0.0224   1.0000
   8.500   0.8499   0.02680   0.01850   0.0032   0.0216   1.0000
   8.750   0.8797   0.02852   0.02038   0.0024   0.0209   1.0000
   9.000   0.9012   0.02969   0.02177   0.0031   0.0202   1.0000
   9.250   0.9220   0.03109   0.02340   0.0037   0.0193   1.0000
   9.500   0.9419   0.03279   0.02533   0.0044   0.0186   1.0000
   9.750   0.9588   0.03466   0.02745   0.0055   0.0181   1.0000
  10.000   0.9718   0.03658   0.02962   0.0071   0.0177   1.0000
  10.250   0.9816   0.03850   0.03177   0.0090   0.0174   1.0000
  10.500   0.9882   0.04057   0.03406   0.0111   0.0172   1.0000
  10.750   0.9908   0.04290   0.03667   0.0136   0.0170   1.0000
  11.000   0.9907   0.04516   0.03916   0.0162   0.0168   1.0000
  11.250   0.9894   0.04725   0.04142   0.0185   0.0166   1.0000
  11.500   0.9860   0.04953   0.04388   0.0208   0.0164   1.0000
  11.750   0.9804   0.05204   0.04654   0.0227   0.0161   1.0000
  12.000   0.9694   0.05531   0.05000   0.0247   0.0159   1.0000
  12.250   0.9549   0.05877   0.05368   0.0264   0.0159   1.0000
  12.500   0.9352   0.06277   0.05795   0.0277   0.0158   1.0000
  12.750   0.9153   0.06722   0.06265   0.0281   0.0157   1.0000
  13.000   0.8930   0.07237   0.06802   0.0276   0.0157   1.0000
  13.250   0.8703   0.07818   0.07401   0.0258   0.0157   1.0000
  13.500   0.8521   0.08406   0.08001   0.0233   0.0158   1.0000
  13.750   0.8280   0.09191   0.08802   0.0188   0.0158   1.0000
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