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FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 60-160 AIRFOIL (fx60160-il)
Reynolds number: 50,000
Max Cl/Cd: 22.66 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60160-il-50000-n5.txt
Download as CSV file: xf-fx60160-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-160 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3991   0.10950   0.10228  -0.0596   1.0000   0.0728
 -11.000  -0.4079   0.10532   0.09817  -0.0602   1.0000   0.0725
 -10.750  -0.4206   0.10067   0.09362  -0.0611   1.0000   0.0724
 -10.500  -0.4366   0.09570   0.08874  -0.0622   1.0000   0.0720
 -10.250  -0.4572   0.09089   0.08401  -0.0630   1.0000   0.0715
 -10.000  -0.4838   0.08640   0.07962  -0.0633   1.0000   0.0708
  -9.750  -0.5149   0.08262   0.07591  -0.0625   1.0000   0.0700
  -9.500  -0.5505   0.07968   0.07303  -0.0606   1.0000   0.0693
  -9.250  -0.5895   0.07745   0.07086  -0.0573   1.0000   0.0683
  -9.000  -0.6068   0.07238   0.06557  -0.0611   0.9915   0.0681
  -8.750  -0.6096   0.06729   0.06014  -0.0650   0.9816   0.0685
  -8.500  -0.6060   0.06276   0.05522  -0.0679   0.9727   0.0691
  -8.250  -0.6002   0.05888   0.05094  -0.0693   0.9639   0.0693
  -8.000  -0.5871   0.05517   0.04677  -0.0710   0.9569   0.0698
  -7.750  -0.5737   0.05210   0.04326  -0.0717   0.9492   0.0707
  -7.500  -0.5531   0.04924   0.03983  -0.0732   0.9435   0.0728
  -7.250  -0.5372   0.04702   0.03705  -0.0729   0.9357   0.0744
  -7.000  -0.5103   0.04458   0.03433  -0.0742   0.9310   0.0758
  -6.750  -0.4884   0.04275   0.03232  -0.0742   0.9250   0.0771
  -6.500  -0.4635   0.04117   0.03056  -0.0744   0.9193   0.0789
  -6.250  -0.4324   0.03978   0.02895  -0.0756   0.9152   0.0824
  -6.000  -0.4112   0.03871   0.02766  -0.0748   0.9086   0.0857
  -5.750  -0.3829   0.03766   0.02635  -0.0748   0.9036   0.0880
  -5.500  -0.3503   0.03661   0.02532  -0.0753   0.9001   0.0907
  -5.250  -0.3316   0.03600   0.02469  -0.0738   0.8934   0.0943
  -5.000  -0.3052   0.03537   0.02394  -0.0737   0.8882   0.0998
  -4.750  -0.2747   0.03460   0.02312  -0.0743   0.8846   0.1054
  -4.500  -0.2621   0.03411   0.02261  -0.0722   0.8768   0.1094
  -4.250  -0.2348   0.03343   0.02181  -0.0726   0.8720   0.1175
  -4.000  -0.2156   0.03276   0.02116  -0.0721   0.8660   0.1284
  -3.750  -0.1950   0.03200   0.02043  -0.0719   0.8599   0.1434
  -3.500  -0.1662   0.03048   0.01926  -0.0737   0.8560   0.1881
  -3.250  -0.1647   0.02933   0.02003  -0.0696   0.8486   0.4675
  -3.000  -0.1438   0.03016   0.02092  -0.0668   0.8432   0.5731
  -2.750  -0.1206   0.03098   0.02157  -0.0649   0.8380   0.6212
  -2.500  -0.1100   0.03199   0.02252  -0.0605   0.8305   0.6566
  -2.250  -0.0889   0.03280   0.02323  -0.0573   0.8261   0.6904
  -2.000  -0.0796   0.03336   0.02372  -0.0532   0.8186   0.7145
  -1.750  -0.0622   0.03368   0.02395  -0.0501   0.8131   0.7353
  -1.500  -0.0317   0.03360   0.02368  -0.0503   0.8095   0.7490
  -1.250  -0.0201   0.03375   0.02370  -0.0485   0.8009   0.7586
  -1.000   0.0073   0.03365   0.02346  -0.0485   0.7962   0.7666
  -0.750   0.0353   0.03357   0.02320  -0.0490   0.7914   0.7763
  -0.500   0.0487   0.03375   0.02331  -0.0470   0.7833   0.7847
  -0.250   0.0799   0.03360   0.02303  -0.0478   0.7791   0.7935
   0.000   0.0962   0.03379   0.02313  -0.0465   0.7716   0.8016
   0.250   0.1210   0.03381   0.02306  -0.0465   0.7655   0.8091
   0.500   0.1556   0.03361   0.02275  -0.0478   0.7619   0.8162
   0.750   0.1660   0.03405   0.02314  -0.0460   0.7525   0.8236
   1.000   0.1967   0.03395   0.02298  -0.0467   0.7477   0.8303
   1.250   0.2181   0.03419   0.02316  -0.0464   0.7408   0.8374
   1.500   0.2400   0.03436   0.02330  -0.0459   0.7337   0.8441
   1.750   0.2759   0.03419   0.02307  -0.0475   0.7300   0.8509
   2.000   0.2854   0.03480   0.02370  -0.0455   0.7200   0.8580
   2.250   0.3183   0.03473   0.02360  -0.0466   0.7154   0.8649
   2.500   0.3342   0.03522   0.02411  -0.0456   0.7068   0.8722
   2.750   0.3623   0.03535   0.02424  -0.0461   0.7008   0.8796
   3.000   0.4001   0.03507   0.02398  -0.0476   0.6975   0.8864
   3.250   0.4085   0.03603   0.02500  -0.0461   0.6863   0.8958
   3.500   0.4464   0.03581   0.02483  -0.0477   0.6825   0.9035
   4.000   0.4986   0.03667   0.02585  -0.0490   0.6675   0.9246
   4.250   0.5192   0.03769   0.02698  -0.0498   0.6570   0.9402
   4.500   0.5614   0.03762   0.02703  -0.0526   0.6523   0.9680
   5.000   0.6064   0.03886   0.02836  -0.0533   0.6367   1.0000
   5.500   0.6516   0.04031   0.02993  -0.0540   0.6213   1.0000
   6.000   0.6958   0.04189   0.03166  -0.0545   0.6057   1.0000
   6.500   0.7383   0.04360   0.03355  -0.0548   0.5900   1.0000
   6.750   0.7454   0.04546   0.03548  -0.0541   0.5788   1.0000
   7.000   0.7789   0.04544   0.03561  -0.0548   0.5743   1.0000
   7.250   0.7843   0.04748   0.03773  -0.0539   0.5628   1.0000
   7.500   0.8191   0.04726   0.03766  -0.0545   0.5585   1.0000
   8.250   0.8949   0.04625   0.03706  -0.0521   0.5245   1.0000
   8.500   0.9261   0.04465   0.03560  -0.0508   0.5093   1.0000
   8.750   0.9486   0.04405   0.03516  -0.0494   0.4936   1.0000
   9.000   0.9614   0.04432   0.03555  -0.0476   0.4751   1.0000
   9.250   0.9787   0.04409   0.03544  -0.0458   0.4548   1.0000
   9.500   0.9943   0.04388   0.03529  -0.0439   0.4293   1.0000
   9.750   1.0031   0.04444   0.03589  -0.0419   0.3969   1.0000
  10.000   1.0101   0.04543   0.03688  -0.0401   0.3611   1.0000
  10.250   1.0166   0.04653   0.03784  -0.0382   0.3096   1.0000
  10.500   1.0173   0.04819   0.03894  -0.0360   0.2296   1.0000
  10.750   1.0069   0.05145   0.04165  -0.0343   0.1798   1.0000
  11.000   0.9986   0.05491   0.04482  -0.0333   0.1530   1.0000
  11.250   0.9941   0.05817   0.04792  -0.0325   0.1372   1.0000
  11.500   0.9930   0.06117   0.05084  -0.0320   0.1266   1.0000
  11.750   0.9929   0.06412   0.05371  -0.0315   0.1193   1.0000
  12.000   0.9974   0.06660   0.05624  -0.0311   0.1127   1.0000
  12.250   1.0020   0.06906   0.05867  -0.0306   0.1081   1.0000
  12.500   1.0118   0.07097   0.06063  -0.0300   0.1044   1.0000
  12.750   1.0245   0.07257   0.06233  -0.0293   0.1008   1.0000
  13.000   1.0398   0.07389   0.06370  -0.0286   0.0976   1.0000
  13.250   1.0612   0.07457   0.06430  -0.0274   0.0940   1.0000
  13.500   1.0812   0.07571   0.06571  -0.0267   0.0905   1.0000
  13.750   1.1044   0.07664   0.06682  -0.0259   0.0867   1.0000
  14.000   1.1408   0.07668   0.06697  -0.0248   0.0836   1.0000
  14.250   1.1860   0.07700   0.06735  -0.0239   0.0799   1.0000
  14.500   1.1896   0.08013   0.07087  -0.0237   0.0778   1.0000
  14.750   1.1938   0.08338   0.07445  -0.0236   0.0755   1.0000
  15.000   1.1979   0.08680   0.07816  -0.0236   0.0735   1.0000
  15.250   1.2003   0.09019   0.08173  -0.0237   0.0709   1.0000
  15.500   1.2103   0.09324   0.08477  -0.0238   0.0672   1.0000
  15.750   1.1889   0.09855   0.09044  -0.0250   0.0663   1.0000
  16.000   1.1679   0.10437   0.09660  -0.0268   0.0654   1.0000
  16.250   1.1460   0.11082   0.10335  -0.0293   0.0646   1.0000
  16.500   1.1222   0.11805   0.11085  -0.0326   0.0641   1.0000
  16.750   1.0953   0.12647   0.11951  -0.0371   0.0640   1.0000
  17.000   1.0645   0.13658   0.12982  -0.0430   0.0645   1.0000
  17.250   1.0311   0.14860   0.14199  -0.0505   0.0654   1.0000
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