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NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-209 (naca66209-il)
Reynolds number: 50,000
Max Cl/Cd: 25.88 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66209-il-50000-n5.txt
Download as CSV file: xf-naca66209-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4214   0.09415   0.08747  -0.0353   1.0000   0.0726
  -9.500  -0.4257   0.08887   0.08221  -0.0374   1.0000   0.0617
  -9.000  -0.5224   0.08915   0.08220  -0.0394   1.0000   0.0620
  -8.750  -0.5317   0.08438   0.07751  -0.0421   1.0000   0.0587
  -8.250  -0.5577   0.07632   0.06942  -0.0437   1.0000   0.0518
  -8.000  -0.5625   0.07289   0.06599  -0.0428   1.0000   0.0506
  -7.750  -0.5690   0.06950   0.06255  -0.0415   1.0000   0.0495
  -7.500  -0.5751   0.06622   0.05918  -0.0398   1.0000   0.0485
  -7.250  -0.5802   0.06296   0.05580  -0.0378   1.0000   0.0475
  -7.000  -0.5839   0.05977   0.05243  -0.0356   1.0000   0.0472
  -6.750  -0.5847   0.05679   0.04924  -0.0333   1.0000   0.0469
  -6.500  -0.5836   0.05385   0.04604  -0.0309   1.0000   0.0479
  -6.250  -0.5798   0.05101   0.04289  -0.0287   1.0000   0.0490
  -6.000  -0.5734   0.04807   0.03958  -0.0265   1.0000   0.0496
  -5.750  -0.5641   0.04514   0.03626  -0.0244   1.0000   0.0495
  -5.500  -0.5521   0.04226   0.03295  -0.0224   1.0000   0.0492
  -5.250  -0.5374   0.03958   0.02983  -0.0206   1.0000   0.0491
  -5.000  -0.5205   0.03708   0.02688  -0.0190   1.0000   0.0494
  -4.750  -0.5015   0.03478   0.02413  -0.0175   1.0000   0.0499
  -4.500  -0.4812   0.03301   0.02177  -0.0159   1.0000   0.0527
  -4.250  -0.4605   0.03109   0.01958  -0.0148   1.0000   0.0558
  -4.000  -0.4385   0.02942   0.01772  -0.0137   1.0000   0.0579
  -3.750  -0.4155   0.02801   0.01612  -0.0124   1.0000   0.0599
  -3.500  -0.3925   0.02686   0.01478  -0.0110   1.0000   0.0625
  -3.250  -0.3704   0.02599   0.01366  -0.0095   1.0000   0.0675
  -3.000  -0.3504   0.02502   0.01268  -0.0083   1.0000   0.0753
  -2.750  -0.3300   0.02425   0.01164  -0.0070   1.0000   0.0814
  -2.500  -0.3107   0.02340   0.01072  -0.0058   1.0000   0.0897
  -2.250  -0.1257   0.02118   0.01147  -0.0255   1.0000   1.0000
  -2.000  -0.1215   0.02106   0.01117  -0.0223   1.0000   1.0000
  -1.750  -0.1172   0.02094   0.01088  -0.0191   1.0000   1.0000
  -1.500  -0.1127   0.02082   0.01061  -0.0160   1.0000   1.0000
  -1.250  -0.1081   0.02071   0.01036  -0.0128   1.0000   1.0000
  -1.000  -0.1032   0.02059   0.01012  -0.0097   1.0000   1.0000
  -0.750  -0.0979   0.02048   0.00986  -0.0066   1.0000   1.0000
  -0.500  -0.0804   0.02049   0.00972  -0.0059   0.9971   1.0000
  -0.250  -0.0546   0.02063   0.00971  -0.0067   0.9919   1.0000
   0.000  -0.0286   0.02081   0.00977  -0.0074   0.9868   1.0000
   0.250  -0.0038   0.02098   0.00983  -0.0079   0.9812   1.0000
   0.500   0.0240   0.02125   0.01001  -0.0090   0.9762   1.0000
   0.750   0.0481   0.02144   0.01015  -0.0093   0.9699   1.0000
   1.000   0.0781   0.02178   0.01045  -0.0107   0.9648   1.0000
   1.500   0.1324   0.02239   0.01105  -0.0123   0.9528   1.0000
   1.750   0.1567   0.02267   0.01135  -0.0125   0.9457   1.0000
   2.000   0.1883   0.02308   0.01182  -0.0140   0.9397   1.0000
   2.250   0.2142   0.02341   0.01226  -0.0145   0.9323   1.0000
   2.500   0.2473   0.02385   0.01281  -0.0162   0.9257   1.0000
   2.750   0.2731   0.02420   0.01329  -0.0166   0.9170   1.0000
   3.000   0.3078   0.02464   0.01392  -0.0185   0.9096   1.0000
   3.250   0.3363   0.02501   0.01453  -0.0192   0.8997   1.0000
   3.500   0.3659   0.02536   0.01512  -0.0200   0.8890   1.0000
   3.750   0.3989   0.02569   0.01576  -0.0212   0.8775   1.0000
   4.000   0.4544   0.02532   0.01595  -0.0249   0.8534   1.0000
   4.250   0.5342   0.02064   0.00943  -0.0190   0.2771   1.0000
   4.500   0.5337   0.02302   0.01059  -0.0152   0.1221   1.0000
   4.750   0.5474   0.02441   0.01178  -0.0131   0.0960   1.0000
   5.000   0.5643   0.02559   0.01300  -0.0115   0.0800   1.0000
   5.250   0.5831   0.02692   0.01435  -0.0101   0.0731   1.0000
   5.500   0.6085   0.02816   0.01584  -0.0093   0.0679   1.0000
   5.750   0.6399   0.02983   0.01748  -0.0098   0.0601   1.0000
   6.000   0.6747   0.03145   0.01943  -0.0102   0.0553   1.0000
   6.250   0.7086   0.03360   0.02183  -0.0107   0.0529   1.0000
   6.500   0.7382   0.03603   0.02462  -0.0106   0.0512   1.0000
   6.750   0.7636   0.03866   0.02756  -0.0101   0.0498   1.0000
   7.000   0.7843   0.04186   0.03097  -0.0095   0.0474   1.0000
   7.250   0.8008   0.04427   0.03405  -0.0076   0.0453   1.0000
   7.500   0.8152   0.04741   0.03771  -0.0058   0.0444   1.0000
   7.750   0.8268   0.05076   0.04153  -0.0040   0.0443   1.0000
   8.000   0.8349   0.05433   0.04553  -0.0020   0.0443   1.0000
   8.250   0.8395   0.05802   0.04963  -0.0001   0.0444   1.0000
   8.500   0.8411   0.06180   0.05377   0.0019   0.0447   1.0000
   8.750   0.8397   0.06565   0.05792   0.0037   0.0450   1.0000
   9.000   0.8355   0.06955   0.06207   0.0053   0.0454   1.0000
   9.250   0.8277   0.07346   0.06619   0.0067   0.0457   1.0000
   9.500   0.8169   0.07719   0.07008   0.0081   0.0459   1.0000
   9.750   0.8026   0.08102   0.07403   0.0091   0.0461   1.0000
  10.000   0.7896   0.08521   0.07830   0.0090   0.0464   1.0000
  10.250   0.7769   0.08979   0.08295   0.0079   0.0467   1.0000
  10.500   0.7681   0.09467   0.08785   0.0063   0.0471   1.0000
  10.750   0.7586   0.10001   0.09322   0.0038   0.0473   1.0000
  11.000   0.7526   0.10548   0.09870   0.0012   0.0475   1.0000
  11.500   0.7247   0.12318   0.11633  -0.0141   0.0566   1.0000
  11.750   0.7252   0.12839   0.12151  -0.0163   0.0578   1.0000
  12.000   0.7276   0.13333   0.12643  -0.0182   0.0587   1.0000
  12.250   0.7311   0.13824   0.13134  -0.0198   0.0594   1.0000
  12.750   0.6069   0.14604   0.13979  -0.0177   0.1280   1.0000
  13.000   0.5921   0.14788   0.14162  -0.0204   0.1273   1.0000
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