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FX 66-S-161 AIRFOIL (fx66s161-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-161 AIRFOIL (fx66s161-il)
Reynolds number: 100,000
Max Cl/Cd: 42.39 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66s161-il-100000-n5.txt
Download as CSV file: xf-fx66s161-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-161 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3306   0.09569   0.09120  -0.0551   1.0000   0.0263
 -10.750  -0.3413   0.08913   0.08473  -0.0581   1.0000   0.0261
 -10.500  -0.3565   0.07818   0.07382  -0.0658   0.9638   0.0257
 -10.250  -0.3931   0.06240   0.05776  -0.0830   0.9136   0.0240
 -10.000  -0.4111   0.05302   0.04785  -0.0957   0.8703   0.0236
  -9.500  -0.4199   0.04660   0.04075  -0.0999   0.8119   0.0246
  -9.250  -0.4207   0.04398   0.03776  -0.0998   0.7937   0.0253
  -9.000  -0.4186   0.04127   0.03464  -0.0994   0.7788   0.0259
  -8.750  -0.4124   0.03860   0.03152  -0.0987   0.7661   0.0267
  -8.500  -0.4014   0.03608   0.02852  -0.0980   0.7550   0.0272
  -8.250  -0.3865   0.03378   0.02575  -0.0973   0.7454   0.0279
  -8.000  -0.3684   0.03182   0.02336  -0.0966   0.7353   0.0286
  -7.750  -0.3483   0.02998   0.02139  -0.0963   0.7268   0.0297
  -7.500  -0.3272   0.02885   0.02015  -0.0959   0.7182   0.0316
  -7.250  -0.3051   0.02776   0.01884  -0.0955   0.7105   0.0342
  -7.000  -0.2820   0.02663   0.01743  -0.0949   0.7033   0.0365
  -6.750  -0.2605   0.02536   0.01611  -0.0943   0.6970   0.0387
  -6.500  -0.2385   0.02454   0.01525  -0.0938   0.6903   0.0424
  -6.250  -0.2154   0.02377   0.01427  -0.0932   0.6850   0.0466
  -6.000  -0.1948   0.02284   0.01336  -0.0925   0.6785   0.0506
  -5.750  -0.1720   0.02221   0.01259  -0.0920   0.6728   0.0575
  -5.500  -0.1501   0.02142   0.01173  -0.0914   0.6677   0.0649
  -5.250  -0.1276   0.02071   0.01100  -0.0910   0.6619   0.0776
  -5.000  -0.1044   0.01997   0.01024  -0.0908   0.6572   0.0999
  -4.750  -0.0823   0.01898   0.00949  -0.0907   0.6530   0.1564
  -4.500  -0.0627   0.01779   0.00904  -0.0905   0.6482   0.3080
  -4.250  -0.0386   0.01768   0.00922  -0.0898   0.6440   0.4017
  -4.000  -0.0118   0.01785   0.00926  -0.0895   0.6403   0.4470
  -3.750   0.0144   0.01808   0.00938  -0.0891   0.6358   0.4785
  -3.500   0.0405   0.01830   0.00949  -0.0886   0.6313   0.5040
  -3.250   0.0667   0.01852   0.00959  -0.0880   0.6275   0.5253
  -3.000   0.0936   0.01868   0.00959  -0.0876   0.6244   0.5431
  -2.750   0.1195   0.01879   0.00965  -0.0872   0.6202   0.5551
  -2.500   0.1464   0.01881   0.00956  -0.0871   0.6162   0.5643
  -2.250   0.1738   0.01880   0.00941  -0.0871   0.6128   0.5717
  -2.000   0.2019   0.01879   0.00922  -0.0872   0.6099   0.5782
  -1.750   0.2284   0.01883   0.00921  -0.0871   0.6059   0.5841
  -1.500   0.2555   0.01887   0.00915  -0.0872   0.6021   0.5914
  -1.250   0.2825   0.01890   0.00911  -0.0871   0.5988   0.5971
  -1.000   0.3105   0.01893   0.00901  -0.0873   0.5960   0.6039
  -0.750   0.3376   0.01899   0.00902  -0.0873   0.5931   0.6096
  -0.500   0.3637   0.01911   0.00913  -0.0872   0.5895   0.6161
  -0.250   0.3906   0.01920   0.00918  -0.0873   0.5862   0.6231
   0.000   0.4177   0.01927   0.00921  -0.0872   0.5832   0.6298
   0.250   0.4458   0.01934   0.00920  -0.0874   0.5807   0.6378
   0.500   0.4719   0.01948   0.00935  -0.0872   0.5777   0.6451
   0.750   0.4973   0.01968   0.00959  -0.0871   0.5743   0.6532
   1.000   0.5231   0.01983   0.00977  -0.0869   0.5713   0.6608
   1.250   0.5500   0.01996   0.00988  -0.0869   0.5684   0.6689
   1.500   0.5773   0.02005   0.00995  -0.0869   0.5660   0.6772
   1.750   0.6038   0.02022   0.01014  -0.0869   0.5632   0.6860
   2.000   0.6277   0.02050   0.01052  -0.0866   0.5594   0.6962
   2.250   0.6529   0.02068   0.01076  -0.0863   0.5559   0.7066
   2.500   0.6795   0.02078   0.01091  -0.0862   0.5528   0.7184
   2.750   0.7071   0.02085   0.01098  -0.0861   0.5503   0.7316
   3.000   0.7299   0.02113   0.01140  -0.0856   0.5465   0.7459
   3.250   0.7526   0.02139   0.01180  -0.0850   0.5426   0.7626
   3.500   0.7770   0.02154   0.01207  -0.0844   0.5394   0.7841
   3.750   0.8021   0.02160   0.01224  -0.0839   0.5369   0.8121
   4.000   0.8287   0.02161   0.01236  -0.0835   0.5349   0.8544
   4.250   0.8590   0.02203   0.01307  -0.0848   0.5305   1.0000
   4.500   0.8832   0.02248   0.01355  -0.0848   0.5268   1.0000
   4.750   0.9101   0.02277   0.01383  -0.0850   0.5237   1.0000
   5.000   0.9386   0.02299   0.01404  -0.0854   0.5213   1.0000
   5.250   0.9614   0.02352   0.01463  -0.0851   0.5180   1.0000
   5.500   0.9799   0.02425   0.01548  -0.0843   0.5136   1.0000
   5.750   1.0038   0.02467   0.01596  -0.0840   0.5102   1.0000
   6.000   1.0312   0.02491   0.01624  -0.0841   0.5074   1.0000
   6.250   1.0607   0.02507   0.01641  -0.0845   0.5053   1.0000
   6.500   1.0696   0.02623   0.01779  -0.0825   0.4993   1.0000
   6.750   1.0910   0.02675   0.01841  -0.0819   0.4954   1.0000
   7.000   1.1180   0.02698   0.01870  -0.0819   0.4925   1.0000
   7.250   1.1483   0.02709   0.01885  -0.0823   0.4903   1.0000
   7.500   1.1481   0.02864   0.02065  -0.0793   0.4834   1.0000
   7.750   1.1691   0.02915   0.02127  -0.0787   0.4797   1.0000
   8.000   1.1971   0.02934   0.02156  -0.0788   0.4771   1.0000
   8.250   1.2045   0.03051   0.02291  -0.0766   0.4719   1.0000
   8.500   1.2106   0.03167   0.02423  -0.0743   0.4664   1.0000
   8.750   1.2370   0.03185   0.02452  -0.0742   0.4633   1.0000
   9.000   1.2724   0.03159   0.02439  -0.0750   0.4610   1.0000
   9.250   1.2320   0.03468   0.02766  -0.0677   0.4514   1.0000
   9.500   1.2655   0.03434   0.02745  -0.0681   0.4484   1.0000
   9.750   1.2096   0.03904   0.03224  -0.0614   0.4375   1.0000
  10.000   1.2437   0.03833   0.03168  -0.0613   0.4345   1.0000
  10.250   1.2816   0.03729   0.03079  -0.0615   0.4308   1.0000
  10.750   1.1907   0.04885   0.04245  -0.0559   0.4057   1.0000
  11.250   1.2080   0.05080   0.04461  -0.0540   0.3859   1.0000
  11.500   1.2146   0.05152   0.04539  -0.0529   0.3685   1.0000
  11.750   1.2286   0.05133   0.04520  -0.0518   0.3437   1.0000
  12.000   1.2270   0.05365   0.04753  -0.0511   0.3229   1.0000
  12.250   1.2339   0.05501   0.04886  -0.0503   0.3015   1.0000
  12.500   1.2269   0.05830   0.05217  -0.0499   0.2792   1.0000
  12.750   1.2274   0.06035   0.05401  -0.0490   0.2417   1.0000
  13.000   1.2181   0.06376   0.05710  -0.0485   0.2018   1.0000
  13.250   1.2033   0.06822   0.06133  -0.0485   0.1691   1.0000
  13.500   1.1862   0.07329   0.06617  -0.0488   0.1393   1.0000
  13.750   1.1701   0.07849   0.07119  -0.0494   0.1119   1.0000
  14.000   1.1562   0.08360   0.07613  -0.0502   0.0884   1.0000
  14.250   1.1448   0.08853   0.08094  -0.0510   0.0705   1.0000
  14.500   1.1361   0.09321   0.08555  -0.0519   0.0573   1.0000
  14.750   1.1293   0.09772   0.09002  -0.0528   0.0483   1.0000
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