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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 50,000
Max Cl/Cd: 30.36 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65209-il-50000-n5.txt
Download as CSV file: xf-naca65209-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5548   0.08274   0.07588  -0.0363   1.0000   0.0503
  -8.500  -0.5592   0.07877   0.07193  -0.0373   1.0000   0.0493
  -8.250  -0.5639   0.07463   0.06778  -0.0385   1.0000   0.0484
  -8.000  -0.5686   0.07042   0.06351  -0.0395   1.0000   0.0475
  -7.750  -0.5714   0.06633   0.05931  -0.0400   1.0000   0.0467
  -7.500  -0.5719   0.06240   0.05521  -0.0402   1.0000   0.0464
  -7.250  -0.5702   0.05863   0.05117  -0.0399   1.0000   0.0467
  -7.000  -0.5663   0.05503   0.04730  -0.0393   1.0000   0.0475
  -6.750  -0.5603   0.05158   0.04351  -0.0383   1.0000   0.0484
  -6.500  -0.5520   0.04823   0.03978  -0.0370   1.0000   0.0489
  -6.250  -0.5412   0.04501   0.03619  -0.0356   1.0000   0.0487
  -6.000  -0.5283   0.04193   0.03269  -0.0342   1.0000   0.0486
  -5.750  -0.5134   0.03910   0.02945  -0.0326   1.0000   0.0488
  -5.500  -0.4967   0.03647   0.02637  -0.0311   1.0000   0.0492
  -5.250  -0.4783   0.03430   0.02369  -0.0295   1.0000   0.0509
  -5.000  -0.4600   0.03212   0.02124  -0.0282   1.0000   0.0540
  -4.750  -0.4406   0.03031   0.01926  -0.0270   1.0000   0.0567
  -4.500  -0.4195   0.02862   0.01728  -0.0255   1.0000   0.0583
  -4.250  -0.3982   0.02717   0.01563  -0.0239   1.0000   0.0604
  -4.000  -0.3773   0.02597   0.01423  -0.0221   1.0000   0.0631
  -3.750  -0.3585   0.02489   0.01309  -0.0205   1.0000   0.0689
  -3.500  -0.3401   0.02403   0.01211  -0.0189   1.0000   0.0758
  -3.250  -0.3217   0.02310   0.01105  -0.0174   1.0000   0.0812
  -3.000  -0.3030   0.02225   0.01005  -0.0162   1.0000   0.0893
  -2.750  -0.2842   0.02137   0.00920  -0.0152   1.0000   0.1086
  -2.500  -0.2665   0.01888   0.00815  -0.0153   1.0000   0.3219
  -2.250  -0.2712   0.01800   0.00907  -0.0065   1.0000   0.7393
  -2.000  -0.2692   0.01825   0.00944   0.0009   1.0000   0.8398
  -1.750  -0.1649   0.01912   0.00975  -0.0080   1.0000   0.9733
  -1.500  -0.1248   0.01898   0.00932  -0.0118   1.0000   0.9864
  -1.250  -0.0922   0.01888   0.00899  -0.0144   1.0000   1.0000
  -1.000  -0.0610   0.01888   0.00877  -0.0167   0.9906   1.0000
  -0.750  -0.0296   0.01894   0.00866  -0.0190   0.9810   1.0000
  -0.500   0.0006   0.01903   0.00861  -0.0209   0.9719   1.0000
  -0.250   0.0320   0.01916   0.00862  -0.0230   0.9634   1.0000
   0.000   0.0600   0.01929   0.00864  -0.0243   0.9542   1.0000
   0.250   0.0873   0.01945   0.00872  -0.0253   0.9452   1.0000
   0.500   0.1208   0.01967   0.00889  -0.0274   0.9381   1.0000
   0.750   0.1460   0.01987   0.00905  -0.0279   0.9288   1.0000
   1.000   0.1778   0.02012   0.00929  -0.0296   0.9215   1.0000
   1.250   0.2068   0.02038   0.00956  -0.0306   0.9133   1.0000
   1.500   0.2356   0.02066   0.00987  -0.0316   0.9053   1.0000
   1.750   0.2686   0.02095   0.01026  -0.0333   0.8981   1.0000
   2.000   0.2953   0.02128   0.01065  -0.0338   0.8893   1.0000
   2.250   0.3309   0.02158   0.01108  -0.0357   0.8827   1.0000
   2.500   0.3553   0.02193   0.01155  -0.0357   0.8729   1.0000
   2.750   0.3855   0.02227   0.01209  -0.0366   0.8645   1.0000
   3.000   0.4170   0.02257   0.01261  -0.0376   0.8557   1.0000
   3.250   0.4434   0.02292   0.01317  -0.0377   0.8448   1.0000
   3.500   0.4728   0.02322   0.01373  -0.0381   0.8339   1.0000
   3.750   0.5047   0.02340   0.01430  -0.0386   0.8218   1.0000
   4.000   0.5552   0.01983   0.01097  -0.0331   0.7212   1.0000
   4.250   0.5708   0.01880   0.00951  -0.0264   0.5403   1.0000
   4.500   0.5675   0.02174   0.00989  -0.0210   0.1558   1.0000
   4.750   0.5808   0.02365   0.01140  -0.0193   0.1044   1.0000
   5.000   0.5975   0.02511   0.01274  -0.0179   0.0853   1.0000
   5.250   0.6167   0.02636   0.01409  -0.0167   0.0747   1.0000
   5.500   0.6374   0.02781   0.01561  -0.0155   0.0695   1.0000
   5.750   0.6640   0.02920   0.01723  -0.0148   0.0646   1.0000
   6.000   0.6921   0.03100   0.01895  -0.0148   0.0580   1.0000
   6.250   0.7233   0.03273   0.02109  -0.0146   0.0540   1.0000
   6.500   0.7538   0.03501   0.02368  -0.0144   0.0520   1.0000
   6.750   0.7810   0.03757   0.02659  -0.0139   0.0505   1.0000
   7.000   0.8049   0.04038   0.02979  -0.0132   0.0493   1.0000
   7.250   0.8252   0.04315   0.03281  -0.0126   0.0471   1.0000
   7.500   0.8411   0.04657   0.03655  -0.0117   0.0447   1.0000
   7.750   0.8544   0.04973   0.04031  -0.0101   0.0436   1.0000
   8.000   0.8650   0.05338   0.04445  -0.0086   0.0434   1.0000
   8.250   0.8721   0.05723   0.04882  -0.0071   0.0433   1.0000
   8.500   0.8760   0.06119   0.05316  -0.0058   0.0434   1.0000
   8.750   0.8765   0.06524   0.05755  -0.0045   0.0436   1.0000
   9.000   0.8735   0.06937   0.06197  -0.0033   0.0438   1.0000
   9.250   0.8679   0.07350   0.06633  -0.0024   0.0441   1.0000
   9.500   0.8592   0.07761   0.07061  -0.0017   0.0443   1.0000
   9.750   0.8466   0.08158   0.07470  -0.0011   0.0445   1.0000
  10.000   0.8351   0.08584   0.07905  -0.0013   0.0448   1.0000
  10.250   0.8231   0.09049   0.08378  -0.0025   0.0450   1.0000
  10.500   0.8134   0.09558   0.08891  -0.0043   0.0453   1.0000
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