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NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M27 AIRFOIL (m27-il)
Reynolds number: 100,000
Max Cl/Cd: 41.3 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m27-il-100000-n5.txt
Download as CSV file: xf-m27-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M27 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1431   0.10540   0.09995  -0.0256   0.6399   0.0432
  -8.000  -0.1391   0.10348   0.09800  -0.0291   0.6369   0.0437
  -7.750  -0.1379   0.10200   0.09650  -0.0325   0.6336   0.0439
  -7.500  -0.1302   0.10035   0.09483  -0.0371   0.6294   0.0440
  -7.250  -0.1181   0.09512   0.08962  -0.0357   0.6253   0.0445
  -7.000  -0.1072   0.09131   0.08577  -0.0351   0.6218   0.0453
  -6.750  -0.0968   0.08845   0.08284  -0.0358   0.6189   0.0467
  -6.500  -0.0843   0.08582   0.08020  -0.0379   0.6146   0.0484
  -6.250  -0.0704   0.08333   0.07768  -0.0405   0.6107   0.0504
  -6.000  -0.0523   0.08159   0.07582  -0.0450   0.6072   0.0519
  -5.750  -0.0299   0.08054   0.07454  -0.0501   0.6043   0.0525
  -5.500  -0.0158   0.07674   0.07070  -0.0507   0.6011   0.0528
  -5.250  -0.0038   0.07283   0.06685  -0.0502   0.5968   0.0536
  -5.000   0.0112   0.06995   0.06393  -0.0505   0.5929   0.0549
  -4.750   0.0293   0.06754   0.06142  -0.0516   0.5897   0.0573
  -4.500   0.0552   0.06597   0.05963  -0.0542   0.5870   0.0609
  -4.250   0.0914   0.06602   0.05933  -0.0585   0.5832   0.0620
  -4.000   0.1059   0.06200   0.05535  -0.0586   0.5792   0.0625
  -3.750   0.1205   0.05867   0.05202  -0.0583   0.5757   0.0634
  -3.500   0.1390   0.05618   0.04942  -0.0583   0.5727   0.0648
  -3.250   0.1605   0.05408   0.04716  -0.0587   0.5702   0.0667
  -3.000   0.1883   0.05286   0.04582  -0.0601   0.5659   0.0713
  -2.750   0.2240   0.05262   0.04521  -0.0619   0.5621   0.0737
  -2.500   0.2402   0.04930   0.04189  -0.0617   0.5589   0.0747
  -2.250   0.2602   0.04701   0.03950  -0.0615   0.5561   0.0760
  -2.000   0.2830   0.04519   0.03751  -0.0614   0.5537   0.0779
  -1.750   0.3077   0.04382   0.03608  -0.0618   0.5492   0.0802
  -1.500   0.3347   0.04265   0.03473  -0.0621   0.5454   0.0834
  -1.250   0.3715   0.04324   0.03483  -0.0625   0.5423   0.0867
  -1.000   0.3917   0.04031   0.03184  -0.0623   0.5399   0.0879
  -0.750   0.4126   0.03831   0.02976  -0.0620   0.5376   0.0906
  -0.250   0.4706   0.03499   0.02592  -0.0616   0.5296   0.0604
   0.000   0.4964   0.03370   0.02446  -0.0614   0.5265   0.0581
   0.250   0.5245   0.03232   0.02278  -0.0610   0.5241   0.0556
   0.750   0.5821   0.02983   0.01961  -0.0604   0.5182   0.0526
   1.000   0.6066   0.02949   0.01931  -0.0605   0.5142   0.0544
   1.250   0.6334   0.02896   0.01864  -0.0604   0.5110   0.0562
   1.500   0.6621   0.02815   0.01760  -0.0604   0.5084   0.0567
   1.750   0.6916   0.02735   0.01655  -0.0603   0.5063   0.0569
   2.000   0.7181   0.02709   0.01622  -0.0605   0.5027   0.0575
   2.250   0.7446   0.02690   0.01597  -0.0607   0.4988   0.0586
   2.500   0.7729   0.02658   0.01554  -0.0609   0.4956   0.0602
   2.750   0.8064   0.02632   0.01520  -0.0621   0.4929   0.0644
   3.000   0.8379   0.02605   0.01482  -0.0627   0.4907   0.0696
   3.250   0.8614   0.02624   0.01496  -0.0625   0.4872   0.0735
   3.500   0.8809   0.02661   0.01542  -0.0617   0.4834   0.0791
   3.750   0.9022   0.02676   0.01554  -0.0609   0.4802   0.0903
   4.000   0.9253   0.02677   0.01553  -0.0603   0.4776   0.1177
   4.250   0.9501   0.02669   0.01550  -0.0598   0.4755   0.1679
   4.500   1.0724   0.02621   0.01641  -0.0803   0.4709   1.0000
   4.750   1.0891   0.02703   0.01724  -0.0792   0.4671   1.0000
   5.000   1.1085   0.02753   0.01771  -0.0783   0.4641   1.0000
   5.250   1.1301   0.02782   0.01792  -0.0775   0.4617   1.0000
   5.500   1.1538   0.02794   0.01795  -0.0769   0.4597   1.0000
   5.750   1.1722   0.02850   0.01850  -0.0759   0.4568   1.0000
   6.000   1.1774   0.02999   0.02013  -0.0737   0.4520   1.0000
   6.250   1.1910   0.03080   0.02096  -0.0722   0.4489   1.0000
   6.500   1.2093   0.03124   0.02141  -0.0711   0.4465   1.0000
   6.750   1.2318   0.03142   0.02154  -0.0704   0.4445   1.0000
   7.000   1.2580   0.03140   0.02146  -0.0700   0.4429   1.0000
   7.250   1.2207   0.03511   0.02547  -0.0637   0.4355   1.0000
   7.500   1.2232   0.03638   0.02677  -0.0611   0.4321   1.0000
   7.750   1.2395   0.03682   0.02722  -0.0597   0.4300   1.0000
   8.000   1.2639   0.03686   0.02726  -0.0592   0.4285   1.0000
   8.250   1.2859   0.03708   0.02747  -0.0584   0.4268   1.0000
   8.750   1.1820   0.04770   0.03829  -0.0474   0.4114   1.0000
  10.250   0.9936   0.08704   0.07807  -0.0421   0.3556   1.0000
  10.500   1.0088   0.08806   0.07914  -0.0416   0.3537   1.0000
  10.750   1.0268   0.08866   0.07976  -0.0410   0.3523   1.0000
  11.000   1.0471   0.08892   0.08006  -0.0405   0.3512   1.0000
  11.500   1.0238   0.09837   0.08964  -0.0406   0.3380   1.0000
  11.750   1.0425   0.09885   0.09018  -0.0401   0.3366   1.0000
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