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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 50,000
Max Cl/Cd: 42.65 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-50000-n5.txt
Download as CSV file: xf-fx60100sm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX60-100 10.0% smoothed                         
  
 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  -0.3886   0.08921   0.08232  -0.0434   1.0000   0.0462
  -8.250  -0.3900   0.08624   0.07945  -0.0429   1.0000   0.0457
  -8.000  -0.3954   0.08321   0.07653  -0.0426   1.0000   0.0451
  -7.750  -0.4036   0.08012   0.07357  -0.0423   1.0000   0.0446
  -7.500  -0.4108   0.07634   0.06990  -0.0432   1.0000   0.0440
  -7.250  -0.4176   0.07199   0.06563  -0.0454   1.0000   0.0434
  -7.000  -0.4243   0.06681   0.06047  -0.0494   1.0000   0.0426
  -6.750  -0.4287   0.06160   0.05519  -0.0535   1.0000   0.0419
  -6.500  -0.4275   0.05629   0.04967  -0.0578   1.0000   0.0413
  -6.250  -0.4187   0.05112   0.04418  -0.0618   1.0000   0.0408
  -6.000  -0.4030   0.04634   0.03895  -0.0655   1.0000   0.0404
  -5.750  -0.3824   0.04227   0.03439  -0.0683   1.0000   0.0406
  -5.500  -0.3592   0.03898   0.03061  -0.0703   1.0000   0.0420
  -5.250  -0.3340   0.03613   0.02723  -0.0719   1.0000   0.0439
  -5.000  -0.3081   0.03374   0.02432  -0.0727   1.0000   0.0454
  -4.750  -0.2827   0.03175   0.02190  -0.0729   1.0000   0.0463
  -4.500  -0.2587   0.02991   0.01983  -0.0727   1.0000   0.0475
  -4.250  -0.2355   0.02845   0.01828  -0.0723   1.0000   0.0495
  -4.000  -0.2116   0.02735   0.01705  -0.0721   1.0000   0.0538
  -3.750  -0.1870   0.02645   0.01589  -0.0718   1.0000   0.0589
  -3.500  -0.1616   0.02534   0.01478  -0.0721   1.0000   0.0644
  -3.250  -0.1239   0.02428   0.01359  -0.0748   0.9955   0.0770
  -3.000  -0.0796   0.02253   0.01220  -0.0793   0.9912   0.1399
  -2.750  -0.0409   0.02192   0.01285  -0.0824   0.9851   0.4313
  -2.500  -0.0119   0.02272   0.01383  -0.0818   0.9762   0.5193
  -2.250   0.0250   0.02289   0.01374  -0.0835   0.9690   0.5461
  -2.000   0.0579   0.02294   0.01359  -0.0845   0.9600   0.5693
  -1.750   0.0937   0.02300   0.01347  -0.0861   0.9521   0.5916
  -1.500   0.1287   0.02303   0.01332  -0.0876   0.9434   0.6120
  -1.250   0.1619   0.02304   0.01321  -0.0887   0.9342   0.6311
  -1.000   0.2002   0.02304   0.01309  -0.0907   0.9265   0.6516
  -0.750   0.2311   0.02304   0.01301  -0.0914   0.9161   0.6703
  -0.500   0.2649   0.02301   0.01294  -0.0925   0.9069   0.6898
  -0.250   0.3015   0.02297   0.01285  -0.0942   0.8982   0.7117
   0.000   0.3308   0.02292   0.01281  -0.0944   0.8873   0.7329
   0.250   0.3636   0.02283   0.01275  -0.0951   0.8776   0.7574
   0.500   0.3978   0.02264   0.01262  -0.0959   0.8687   0.7857
   0.750   0.4235   0.02248   0.01256  -0.0952   0.8568   0.8191
   1.000   0.4504   0.02221   0.01243  -0.0946   0.8453   0.8744
   1.250   0.4879   0.02206   0.01228  -0.0965   0.8336   1.0000
   1.500   0.5298   0.02206   0.01218  -0.0991   0.8244   1.0000
   1.750   0.5631   0.02219   0.01225  -0.1002   0.8115   1.0000
   2.000   0.5959   0.02230   0.01232  -0.1010   0.7985   1.0000
   2.250   0.6283   0.02239   0.01240  -0.1017   0.7854   1.0000
   2.500   0.6603   0.02246   0.01246  -0.1021   0.7719   1.0000
   2.750   0.6920   0.02250   0.01252  -0.1024   0.7579   1.0000
   3.000   0.7231   0.02254   0.01261  -0.1025   0.7434   1.0000
   3.250   0.7538   0.02256   0.01267  -0.1025   0.7281   1.0000
   3.500   0.7843   0.02258   0.01272  -0.1023   0.7121   1.0000
   3.750   0.8147   0.02257   0.01275  -0.1021   0.6955   1.0000
   4.000   0.8435   0.02263   0.01290  -0.1016   0.6771   1.0000
   4.250   0.8705   0.02274   0.01308  -0.1008   0.6564   1.0000
   4.500   0.9000   0.02272   0.01307  -0.1002   0.6358   1.0000
   4.750   0.9250   0.02290   0.01330  -0.0991   0.6106   1.0000
   5.000   0.9504   0.02305   0.01351  -0.0979   0.5837   1.0000
   5.250   0.9748   0.02325   0.01371  -0.0967   0.5540   1.0000
   5.500   0.9982   0.02354   0.01396  -0.0953   0.5223   1.0000
   5.750   1.0205   0.02393   0.01433  -0.0938   0.4892   1.0000
   6.000   1.0409   0.02446   0.01484  -0.0923   0.4537   1.0000
   6.250   1.0606   0.02507   0.01537  -0.0907   0.4175   1.0000
   6.500   1.0786   0.02583   0.01608  -0.0890   0.3790   1.0000
   6.750   1.0954   0.02673   0.01687  -0.0873   0.3397   1.0000
   7.000   1.1109   0.02780   0.01782  -0.0856   0.3017   1.0000
   7.250   1.1260   0.02901   0.01892  -0.0839   0.2660   1.0000
   7.500   1.1408   0.03035   0.02015  -0.0823   0.2363   1.0000
   7.750   1.1555   0.03178   0.02148  -0.0808   0.2116   1.0000
   8.000   1.1708   0.03324   0.02290  -0.0794   0.1913   1.0000
   8.250   1.1877   0.03474   0.02443  -0.0781   0.1760   1.0000
   8.500   1.2047   0.03625   0.02597  -0.0769   0.1622   1.0000
   8.750   1.2219   0.03779   0.02760  -0.0758   0.1498   1.0000
   9.000   1.2413   0.03943   0.02935  -0.0748   0.1401   1.0000
   9.250   1.2598   0.04110   0.03103  -0.0738   0.1312   1.0000
   9.500   1.2761   0.04283   0.03299  -0.0727   0.1219   1.0000
   9.750   1.2949   0.04480   0.03519  -0.0717   0.1144   1.0000
  10.000   1.3102   0.04669   0.03721  -0.0706   0.1070   1.0000
  10.250   1.3218   0.04892   0.03974  -0.0691   0.0998   1.0000
  10.500   1.3338   0.05098   0.04191  -0.0677   0.0936   1.0000
  10.750   1.3386   0.05354   0.04480  -0.0658   0.0879   1.0000
  11.000   1.3412   0.05585   0.04733  -0.0638   0.0824   1.0000
  11.250   1.3459   0.05846   0.05005  -0.0622   0.0777   1.0000
  11.500   1.3380   0.06179   0.05384  -0.0601   0.0738   1.0000
  11.750   1.3341   0.06471   0.05695  -0.0587   0.0700   1.0000
  12.000   1.3362   0.06754   0.05978  -0.0577   0.0664   1.0000
  12.250   1.3189   0.07227   0.06498  -0.0569   0.0647   1.0000
  12.500   1.3007   0.07745   0.07053  -0.0570   0.0631   1.0000
  12.750   1.2810   0.08319   0.07659  -0.0581   0.0620   1.0000
  13.000   1.2587   0.08979   0.08347  -0.0603   0.0614   1.0000
  13.250   1.2319   0.09781   0.09175  -0.0640   0.0616   1.0000
  13.500   1.2000   0.10780   0.10195  -0.0696   0.0629   1.0000
  13.750   1.1674   0.11923   0.11353  -0.0768   0.0643   1.0000
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