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FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 60-160 AIRFOIL (fx60160-il)
Reynolds number: 200,000
Max Cl/Cd: 72.33 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60160-il-200000.txt
Download as CSV file: xf-fx60160-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2808   0.09113   0.08793  -0.0664   0.9848   0.0817
 -10.250  -0.2778   0.08530   0.08210  -0.0709   0.9827   0.0857
 -10.000  -0.3331   0.07070   0.06750  -0.0839   0.9764   0.0889
  -9.750  -0.5241   0.07294   0.06907  -0.0902   0.9706   0.0764
  -9.500  -0.4953   0.06550   0.06194  -0.0906   0.9716   0.0792
  -9.250  -0.4739   0.06251   0.05893  -0.0932   0.9667   0.0818
  -9.000  -0.4725   0.05811   0.05423  -0.0987   0.9563   0.0874
  -8.750  -0.4827   0.05321   0.04893  -0.1012   0.9439   0.0923
  -8.500  -0.4499   0.05045   0.04626  -0.1037   0.9419   0.0967
  -8.250  -0.4627   0.03939   0.03367  -0.1025   0.9288   0.0622
  -8.000  -0.4343   0.03556   0.02946  -0.1048   0.9261   0.0615
  -7.750  -0.4162   0.03304   0.02662  -0.1042   0.9183   0.0613
  -7.500  -0.3868   0.03030   0.02355  -0.1055   0.9142   0.0607
  -7.250  -0.3520   0.02818   0.02111  -0.1075   0.9117   0.0614
  -7.000  -0.3153   0.02680   0.01941  -0.1095   0.9097   0.0631
  -6.750  -0.2967   0.02590   0.01832  -0.1080   0.9006   0.0636
  -6.500  -0.2628   0.02378   0.01605  -0.1094   0.8976   0.0646
  -6.250  -0.2271   0.02199   0.01427  -0.1112   0.8954   0.0671
  -6.000  -0.2042   0.02124   0.01351  -0.1105   0.8885   0.0694
  -5.750  -0.1740   0.02034   0.01256  -0.1110   0.8838   0.0715
  -5.500  -0.1403   0.01942   0.01159  -0.1122   0.8807   0.0740
  -5.250  -0.1150   0.01891   0.01100  -0.1118   0.8746   0.0763
  -5.000  -0.0921   0.01788   0.01004  -0.1113   0.8688   0.0803
  -4.750  -0.0615   0.01713   0.00930  -0.1121   0.8651   0.0849
  -4.500  -0.0392   0.01671   0.00882  -0.1114   0.8585   0.0890
  -4.250  -0.0147   0.01603   0.00817  -0.1112   0.8528   0.0962
  -4.000   0.0161   0.01541   0.00753  -0.1122   0.8491   0.1094
  -3.750   0.0359   0.01487   0.00715  -0.1112   0.8421   0.1436
  -3.500   0.0469   0.01291   0.00686  -0.1096   0.8362   0.5190
  -3.250   0.0786   0.01317   0.00721  -0.1096   0.8328   0.5877
  -3.000   0.1000   0.01361   0.00762  -0.1080   0.8257   0.6127
  -2.750   0.1287   0.01404   0.00801  -0.1075   0.8208   0.6326
  -2.500   0.1611   0.01436   0.00825  -0.1078   0.8172   0.6472
  -2.250   0.1825   0.01475   0.00861  -0.1063   0.8103   0.6598
  -2.000   0.2101   0.01506   0.00888  -0.1057   0.8052   0.6717
  -1.750   0.2411   0.01533   0.00911  -0.1056   0.8013   0.6809
  -1.500   0.2618   0.01564   0.00942  -0.1040   0.7945   0.6920
  -1.250   0.2881   0.01587   0.00963  -0.1032   0.7892   0.7011
  -1.000   0.3193   0.01589   0.00957  -0.1036   0.7853   0.7088
  -0.750   0.3401   0.01602   0.00972  -0.1023   0.7785   0.7139
  -0.500   0.3689   0.01597   0.00957  -0.1028   0.7731   0.7211
  -0.250   0.3998   0.01592   0.00945  -0.1032   0.7692   0.7247
   0.000   0.4204   0.01601   0.00958  -0.1019   0.7623   0.7292
   0.250   0.4490   0.01601   0.00950  -0.1023   0.7570   0.7368
   0.500   0.4788   0.01599   0.00946  -0.1023   0.7530   0.7418
   0.750   0.4986   0.01612   0.00964  -0.1009   0.7459   0.7484
   1.000   0.5268   0.01608   0.00955  -0.1011   0.7406   0.7542
   1.250   0.5579   0.01602   0.00945  -0.1016   0.7365   0.7579
   1.500   0.5777   0.01610   0.00959  -0.1003   0.7291   0.7626
   1.750   0.6078   0.01606   0.00949  -0.1010   0.7239   0.7677
   2.000   0.6355   0.01602   0.00946  -0.1010   0.7188   0.7710
   2.250   0.6574   0.01606   0.00956  -0.1000   0.7118   0.7751
   2.500   0.6878   0.01601   0.00947  -0.1006   0.7068   0.7795
   2.750   0.7135   0.01608   0.00955  -0.1005   0.7003   0.7839
   3.000   0.7380   0.01603   0.00955  -0.0999   0.6938   0.7874
   3.250   0.7698   0.01597   0.00946  -0.1006   0.6892   0.7913
   3.500   0.7901   0.01608   0.00967  -0.0994   0.6813   0.7956
   3.750   0.8201   0.01604   0.00961  -0.1000   0.6754   0.7996
   4.000   0.8432   0.01602   0.00966  -0.0991   0.6677   0.8033
   4.250   0.8710   0.01584   0.00948  -0.0990   0.6593   0.8073
   4.500   0.8937   0.01576   0.00945  -0.0980   0.6490   0.8115
   4.750   0.9220   0.01556   0.00922  -0.0980   0.6392   0.8155
   5.000   0.9444   0.01535   0.00905  -0.0967   0.6276   0.8194
   5.250   0.9649   0.01525   0.00901  -0.0953   0.6155   0.8237
   5.500   0.9882   0.01519   0.00897  -0.0944   0.6041   0.8280
   5.750   1.0102   0.01506   0.00886  -0.0932   0.5913   0.8320
   6.000   1.0316   0.01498   0.00881  -0.0919   0.5784   0.8365
   6.250   1.0503   0.01496   0.00881  -0.0901   0.5631   0.8413
   6.500   1.0663   0.01498   0.00886  -0.0879   0.5446   0.8460
   6.750   1.0803   0.01500   0.00893  -0.0852   0.5248   0.8509
   7.000   1.0937   0.01512   0.00902  -0.0825   0.5034   0.8567
   7.250   1.1019   0.01530   0.00916  -0.0788   0.4773   0.8623
   7.500   1.1060   0.01558   0.00938  -0.0744   0.4480   0.8689
   7.750   1.1050   0.01620   0.00981  -0.0694   0.4072   0.8769
   8.000   1.0965   0.01718   0.01052  -0.0635   0.3480   0.8866
   8.250   1.0788   0.01887   0.01175  -0.0571   0.2612   0.8996
   8.500   1.0585   0.02171   0.01398  -0.0521   0.1503   0.9304
   8.750   1.0497   0.02379   0.01575  -0.0484   0.1087   1.0000
   9.000   1.0511   0.02559   0.01745  -0.0462   0.0970   1.0000
   9.250   1.0580   0.02709   0.01900  -0.0447   0.0912   1.0000
   9.500   1.0614   0.02887   0.02077  -0.0429   0.0869   1.0000
   9.750   1.0627   0.03086   0.02276  -0.0411   0.0838   1.0000
  10.000   1.0721   0.03232   0.02430  -0.0400   0.0815   1.0000
  10.250   1.0806   0.03388   0.02591  -0.0388   0.0794   1.0000
  10.500   1.0897   0.03541   0.02747  -0.0377   0.0775   1.0000
  10.750   1.0997   0.03691   0.02899  -0.0367   0.0758   1.0000
  11.000   1.1113   0.03834   0.03041  -0.0356   0.0741   1.0000
  11.250   1.1283   0.03957   0.03157  -0.0347   0.0721   1.0000
  11.500   1.1509   0.04052   0.03254  -0.0341   0.0705   1.0000
  11.750   1.1685   0.04158   0.03369  -0.0335   0.0692   1.0000
  12.000   1.1863   0.04268   0.03487  -0.0329   0.0673   1.0000
  12.250   1.2022   0.04388   0.03613  -0.0323   0.0650   1.0000
  12.500   1.2171   0.04516   0.03741  -0.0318   0.0622   1.0000
  12.750   1.2435   0.04642   0.03865  -0.0318   0.0586   1.0000
  13.000   1.2508   0.04792   0.04031  -0.0309   0.0570   1.0000
  13.250   1.2622   0.04940   0.04191  -0.0301   0.0549   1.0000
  13.500   1.2730   0.05093   0.04352  -0.0295   0.0529   1.0000
  13.750   1.2872   0.05238   0.04495  -0.0291   0.0506   1.0000
  14.000   1.3022   0.05428   0.04698  -0.0286   0.0480   1.0000
  14.250   1.3018   0.05638   0.04928  -0.0277   0.0459   1.0000
  14.500   1.3039   0.05844   0.05145  -0.0270   0.0437   1.0000
  14.750   1.3101   0.06028   0.05327  -0.0267   0.0417   1.0000
  15.000   1.3150   0.06299   0.05616  -0.0260   0.0391   1.0000
  15.250   1.3134   0.06576   0.05914  -0.0255   0.0370   1.0000
  15.500   1.3142   0.06830   0.06178  -0.0253   0.0353   1.0000
  15.750   1.3286   0.07037   0.06376  -0.0251   0.0332   1.0000
  16.000   1.3166   0.07430   0.06804  -0.0249   0.0321   1.0000
  16.250   1.3095   0.07813   0.07213  -0.0250   0.0308   1.0000
  16.500   1.3066   0.08152   0.07568  -0.0253   0.0297   1.0000
  16.750   1.3048   0.08464   0.07890  -0.0258   0.0288   1.0000
  17.000   1.3070   0.08731   0.08158  -0.0264   0.0279   1.0000
  17.250   1.3065   0.09102   0.08537  -0.0269   0.0271   1.0000
  17.500   1.2901   0.09664   0.09131  -0.0283   0.0267   1.0000
  17.750   1.2717   0.10285   0.09784  -0.0303   0.0264   1.0000
  18.000   1.2518   0.10959   0.10486  -0.0329   0.0261   1.0000
  18.250   1.2301   0.11691   0.11247  -0.0361   0.0260   1.0000
  18.500   1.2073   0.12482   0.12062  -0.0401   0.0259   1.0000
  18.750   1.1819   0.13361   0.12966  -0.0450   0.0260   1.0000
  19.000   1.1541   0.14345   0.13972  -0.0509   0.0262   1.0000
  19.250   1.1258   0.15405   0.15051  -0.0577   0.0265   1.0000
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