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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 50,000
Max Cl/Cd: 30.13 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64206-il-50000-n5.txt
Download as CSV file: xf-naca64206-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5821   0.10395   0.09736  -0.0080   1.0000   0.0999
  -8.250  -0.5653   0.09902   0.09227  -0.0048   1.0000   0.1100
  -8.000  -0.5771   0.09616   0.08970  -0.0108   1.0000   0.1130
  -7.750  -0.5641   0.09192   0.08533  -0.0079   1.0000   0.1227
  -7.250  -0.5625   0.08430   0.07783  -0.0148   1.0000   0.1387
  -6.750  -0.4833   0.05735   0.05099  -0.0285   1.0000   0.0581
  -6.500  -0.5242   0.06563   0.05872  -0.0295   1.0000   0.0558
  -6.250  -0.5123   0.06082   0.05375  -0.0316   1.0000   0.0517
  -6.000  -0.4945   0.05598   0.04844  -0.0341   1.0000   0.0449
  -5.750  -0.4792   0.05172   0.04401  -0.0349   1.0000   0.0431
  -5.500  -0.4614   0.04758   0.03956  -0.0357   1.0000   0.0414
  -5.250  -0.4413   0.04361   0.03519  -0.0363   1.0000   0.0401
  -5.000  -0.4193   0.03984   0.03094  -0.0365   1.0000   0.0391
  -4.750  -0.3959   0.03646   0.02706  -0.0365   1.0000   0.0387
  -4.500  -0.3714   0.03335   0.02343  -0.0361   1.0000   0.0389
  -4.250  -0.3465   0.03082   0.02042  -0.0356   1.0000   0.0419
  -4.000  -0.3203   0.02872   0.01769  -0.0349   1.0000   0.0470
  -3.750  -0.2959   0.02625   0.01501  -0.0340   1.0000   0.0491
  -3.500  -0.2713   0.02432   0.01287  -0.0327   1.0000   0.0516
  -3.250  -0.2476   0.02275   0.01109  -0.0312   1.0000   0.0548
  -3.000  -0.2240   0.02146   0.00939  -0.0297   1.0000   0.0591
  -2.750  -0.2012   0.02035   0.00815  -0.0289   1.0000   0.0732
  -2.500  -0.1779   0.01910   0.00690  -0.0283   1.0000   0.0912
  -2.250  -0.1533   0.01742   0.00561  -0.0282   1.0000   0.1601
  -2.000  -0.1191   0.01439   0.00551  -0.0242   1.0000   1.0000
  -1.750  -0.1033   0.01426   0.00502  -0.0227   1.0000   1.0000
  -1.500  -0.0847   0.01419   0.00453  -0.0216   1.0000   1.0000
  -1.250  -0.0645   0.01415   0.00420  -0.0209   1.0000   1.0000
  -1.000  -0.0433   0.01415   0.00395  -0.0202   1.0000   1.0000
  -0.750  -0.0216   0.01418   0.00377  -0.0197   1.0000   1.0000
  -0.500   0.0003   0.01425   0.00366  -0.0192   1.0000   1.0000
  -0.250   0.0225   0.01434   0.00361  -0.0187   1.0000   1.0000
   0.000   0.0446   0.01447   0.00358  -0.0183   1.0000   1.0000
   0.250   0.0667   0.01462   0.00365  -0.0179   1.0000   1.0000
   0.500   0.0887   0.01481   0.00377  -0.0175   1.0000   1.0000
   0.750   0.1105   0.01503   0.00395  -0.0172   1.0000   1.0000
   1.000   0.1320   0.01528   0.00420  -0.0169   1.0000   1.0000
   1.250   0.1542   0.01557   0.00452  -0.0168   0.9994   1.0000
   1.500   0.1946   0.01599   0.00501  -0.0202   0.9875   1.0000
   1.750   0.2344   0.01638   0.00553  -0.0234   0.9756   1.0000
   2.000   0.2734   0.01676   0.00609  -0.0263   0.9633   1.0000
   2.250   0.3125   0.01714   0.00677  -0.0292   0.9509   1.0000
   2.500   0.3520   0.01751   0.00742  -0.0321   0.9384   1.0000
   2.750   0.3918   0.01787   0.00814  -0.0348   0.9250   1.0000
   3.000   0.4328   0.01817   0.00889  -0.0375   0.9090   1.0000
   3.250   0.4954   0.01644   0.00765  -0.0358   0.7582   1.0000
   3.500   0.5044   0.01747   0.00691  -0.0278   0.3508   1.0000
   3.750   0.5158   0.02091   0.00852  -0.0264   0.0981   1.0000
   4.000   0.5385   0.02246   0.01004  -0.0257   0.0729   1.0000
   4.250   0.5613   0.02403   0.01176  -0.0248   0.0641   1.0000
   4.500   0.5867   0.02566   0.01367  -0.0237   0.0591   1.0000
   4.750   0.6144   0.02759   0.01581  -0.0227   0.0544   1.0000
   5.000   0.6411   0.02966   0.01826  -0.0221   0.0454   1.0000
   5.250   0.6686   0.03214   0.02108  -0.0214   0.0417   1.0000
   5.500   0.6945   0.03508   0.02440  -0.0206   0.0400   1.0000
   5.750   0.7183   0.03848   0.02822  -0.0198   0.0389   1.0000
   6.000   0.7399   0.04222   0.03244  -0.0190   0.0384   1.0000
   6.250   0.7573   0.04667   0.03730  -0.0183   0.0373   1.0000
   6.500   0.7747   0.04991   0.04130  -0.0172   0.0356   1.0000
   6.750   0.7884   0.05388   0.04588  -0.0165   0.0338   1.0000
   7.000   0.7989   0.05828   0.05073  -0.0161   0.0331   1.0000
   7.250   0.8067   0.06286   0.05566  -0.0160   0.0335   1.0000
   7.500   0.8114   0.06756   0.06065  -0.0163   0.0340   1.0000
   7.750   0.8135   0.07226   0.06556  -0.0168   0.0346   1.0000
   8.000   0.8127   0.07706   0.07052  -0.0177   0.0351   1.0000
   8.250   0.8104   0.08178   0.07534  -0.0188   0.0357   1.0000
   8.500   0.8074   0.08647   0.08009  -0.0199   0.0363   1.0000
   9.000   0.7922   0.09668   0.09043  -0.0267   0.0397   1.0000
   9.250   0.7849   0.10381   0.09751  -0.0335   0.0417   1.0000
   9.500   0.7819   0.10972   0.10336  -0.0375   0.0437   1.0000
   9.750   0.7817   0.11508   0.10867  -0.0403   0.0461   1.0000
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