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FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 60-160 AIRFOIL (fx60160-il)
Reynolds number: 100,000
Max Cl/Cd: 48.81 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60160-il-100000-n5.txt
Download as CSV file: xf-fx60160-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4457   0.09044   0.08548  -0.0653   1.0000   0.0379
 -11.000  -0.4761   0.08275   0.07783  -0.0683   1.0000   0.0375
 -10.750  -0.5098   0.07693   0.07202  -0.0697   1.0000   0.0373
 -10.500  -0.5370   0.06968   0.06464  -0.0754   0.9953   0.0370
 -10.250  -0.5566   0.06262   0.05730  -0.0827   0.9853   0.0371
 -10.000  -0.5723   0.05741   0.05176  -0.0873   0.9731   0.0374
  -9.750  -0.5781   0.05244   0.04635  -0.0900   0.9611   0.0380
  -9.500  -0.5838   0.04806   0.04129  -0.0911   0.9489   0.0395
  -9.250  -0.5591   0.04582   0.03905  -0.0935   0.9449   0.0413
  -9.000  -0.5454   0.04416   0.03726  -0.0933   0.9353   0.0427
  -8.750  -0.5230   0.04173   0.03450  -0.0952   0.9305   0.0450
  -8.500  -0.5114   0.03966   0.03200  -0.0943   0.9204   0.0472
  -8.250  -0.4867   0.03730   0.02905  -0.0956   0.9158   0.0490
  -8.000  -0.4704   0.03529   0.02687  -0.0949   0.9072   0.0506
  -7.750  -0.4423   0.03370   0.02517  -0.0962   0.9029   0.0527
  -7.500  -0.4145   0.03213   0.02339  -0.0970   0.8982   0.0543
  -7.250  -0.3917   0.03079   0.02184  -0.0966   0.8910   0.0555
  -7.000  -0.3603   0.02943   0.02026  -0.0977   0.8874   0.0574
  -6.750  -0.3354   0.02848   0.01911  -0.0975   0.8812   0.0596
  -6.500  -0.3075   0.02755   0.01798  -0.0978   0.8758   0.0611
  -6.250  -0.2758   0.02613   0.01656  -0.0987   0.8726   0.0627
  -6.000  -0.2524   0.02526   0.01571  -0.0982   0.8663   0.0643
  -5.750  -0.2258   0.02446   0.01490  -0.0982   0.8612   0.0662
  -5.500  -0.1951   0.02367   0.01408  -0.0991   0.8577   0.0693
  -5.250  -0.1738   0.02318   0.01351  -0.0982   0.8508   0.0725
  -5.000  -0.1477   0.02251   0.01279  -0.0982   0.8458   0.0753
  -4.750  -0.1183   0.02172   0.01198  -0.0990   0.8424   0.0790
  -4.500  -0.0991   0.02132   0.01153  -0.0979   0.8350   0.0829
  -4.250  -0.0711   0.02080   0.01090  -0.0983   0.8304   0.0888
  -4.000  -0.0400   0.02012   0.01024  -0.0994   0.8271   0.1023
  -3.750  -0.0221   0.01965   0.00992  -0.0982   0.8198   0.1282
  -3.500  -0.0034   0.01784   0.00919  -0.0983   0.8148   0.3533
  -3.250   0.0223   0.01749   0.00955  -0.0976   0.8114   0.5139
  -3.000   0.0410   0.01788   0.01001  -0.0955   0.8042   0.5651
  -2.750   0.0697   0.01824   0.01030  -0.0950   0.7998   0.5999
  -2.500   0.1020   0.01856   0.01051  -0.0953   0.7965   0.6270
  -2.250   0.1205   0.01903   0.01095  -0.0931   0.7894   0.6437
  -2.000   0.1472   0.01938   0.01123  -0.0922   0.7847   0.6602
  -1.750   0.1786   0.01952   0.01126  -0.0925   0.7812   0.6736
  -1.500   0.1985   0.01969   0.01138  -0.0910   0.7745   0.6809
  -1.250   0.2268   0.01964   0.01121  -0.0913   0.7694   0.6873
  -1.000   0.2586   0.01958   0.01106  -0.0919   0.7658   0.6923
  -0.750   0.2799   0.01968   0.01109  -0.0911   0.7590   0.7001
  -0.500   0.3060   0.01972   0.01109  -0.0906   0.7538   0.7056
  -0.250   0.3380   0.01966   0.01094  -0.0913   0.7499   0.7130
   0.000   0.3575   0.01979   0.01107  -0.0899   0.7429   0.7190
   0.250   0.3845   0.01978   0.01102  -0.0898   0.7377   0.7236
   0.500   0.4178   0.01967   0.01082  -0.0910   0.7339   0.7291
   0.750   0.4361   0.01982   0.01098  -0.0895   0.7264   0.7337
   1.000   0.4640   0.01979   0.01093  -0.0895   0.7213   0.7376
   1.250   0.4947   0.01973   0.01083  -0.0902   0.7170   0.7423
   1.500   0.5145   0.01990   0.01100  -0.0891   0.7095   0.7474
   1.750   0.5436   0.01983   0.01094  -0.0893   0.7047   0.7508
   2.000   0.5674   0.01991   0.01103  -0.0887   0.6987   0.7550
   2.250   0.5916   0.01999   0.01112  -0.0883   0.6921   0.7598
   2.500   0.6240   0.01991   0.01103  -0.0892   0.6877   0.7637
   2.750   0.6415   0.02010   0.01130  -0.0876   0.6801   0.7675
   3.000   0.6694   0.02010   0.01131  -0.0876   0.6745   0.7717
   3.250   0.6954   0.02018   0.01142  -0.0875   0.6685   0.7763
   3.500   0.7171   0.02030   0.01161  -0.0866   0.6613   0.7801
   3.750   0.7489   0.02021   0.01154  -0.0873   0.6567   0.7839
   4.000   0.7648   0.02048   0.01192  -0.0855   0.6482   0.7885
   4.250   0.7953   0.02047   0.01193  -0.0861   0.6426   0.7929
   4.500   0.8139   0.02066   0.01223  -0.0846   0.6350   0.7967
   4.750   0.8406   0.02070   0.01233  -0.0844   0.6285   0.8010
   5.000   0.8634   0.02087   0.01259  -0.0838   0.6211   0.8056
   5.250   0.8888   0.02088   0.01267  -0.0834   0.6131   0.8099
   5.500   0.9077   0.02096   0.01285  -0.0818   0.6025   0.8144
   5.750   0.9317   0.02087   0.01282  -0.0810   0.5912   0.8193
   6.000   0.9532   0.02077   0.01276  -0.0797   0.5774   0.8241
   6.250   0.9706   0.02073   0.01278  -0.0777   0.5618   0.8291
   6.500   0.9864   0.02077   0.01286  -0.0755   0.5446   0.8350
   6.750   1.0008   0.02084   0.01299  -0.0731   0.5273   0.8407
   7.000   1.0153   0.02096   0.01314  -0.0707   0.5093   0.8471
   7.250   1.0308   0.02112   0.01331  -0.0686   0.4893   0.8541
   7.500   1.0409   0.02148   0.01369  -0.0657   0.4655   0.8624
   7.750   1.0515   0.02189   0.01407  -0.0630   0.4383   0.8721
   8.000   1.0613   0.02244   0.01461  -0.0604   0.4091   0.8849
   8.250   1.0687   0.02324   0.01535  -0.0579   0.3694   0.9084
   8.500   1.0657   0.02441   0.01628  -0.0541   0.3177   1.0000
   8.750   1.0544   0.02653   0.01790  -0.0501   0.2403   1.0000
   9.000   1.0389   0.02931   0.02010  -0.0463   0.1642   1.0000
   9.250   1.0302   0.03196   0.02233  -0.0436   0.1124   1.0000
   9.500   1.0301   0.03410   0.02430  -0.0417   0.0964   1.0000
   9.750   1.0342   0.03598   0.02617  -0.0403   0.0890   1.0000
  10.000   1.0384   0.03789   0.02813  -0.0390   0.0841   1.0000
  10.250   1.0403   0.04003   0.03029  -0.0377   0.0805   1.0000
  10.500   1.0458   0.04192   0.03226  -0.0367   0.0779   1.0000
  10.750   1.0517   0.04380   0.03425  -0.0357   0.0754   1.0000
  11.000   1.0574   0.04573   0.03627  -0.0348   0.0733   1.0000
  11.250   1.0632   0.04768   0.03829  -0.0339   0.0714   1.0000
  11.500   1.0697   0.04958   0.04023  -0.0331   0.0697   1.0000
  11.750   1.0772   0.05140   0.04205  -0.0322   0.0680   1.0000
  12.000   1.0890   0.05285   0.04351  -0.0313   0.0663   1.0000
  12.250   1.1030   0.05417   0.04494  -0.0307   0.0648   1.0000
  12.500   1.1178   0.05546   0.04632  -0.0301   0.0630   1.0000
  12.750   1.1336   0.05671   0.04764  -0.0295   0.0613   1.0000
  13.000   1.1514   0.05785   0.04884  -0.0289   0.0599   1.0000
  13.250   1.1706   0.05896   0.05002  -0.0284   0.0587   1.0000
  13.500   1.1913   0.06005   0.05115  -0.0279   0.0575   1.0000
  13.750   1.2156   0.06107   0.05218  -0.0275   0.0562   1.0000
  14.000   1.2443   0.06221   0.05333  -0.0273   0.0547   1.0000
  14.250   1.2538   0.06419   0.05555  -0.0267   0.0537   1.0000
  14.500   1.2641   0.06627   0.05786  -0.0263   0.0525   1.0000
  14.750   1.2750   0.06847   0.06031  -0.0259   0.0514   1.0000
  15.000   1.2820   0.07089   0.06294  -0.0255   0.0502   1.0000
  15.250   1.2849   0.07349   0.06574  -0.0252   0.0488   1.0000
  15.500   1.2867   0.07612   0.06851  -0.0251   0.0474   1.0000
  15.750   1.2914   0.07853   0.07097  -0.0251   0.0459   1.0000
  16.000   1.2995   0.08116   0.07363  -0.0252   0.0444   1.0000
  16.250   1.2869   0.08524   0.07805  -0.0255   0.0435   1.0000
  16.500   1.2746   0.08960   0.08273  -0.0261   0.0425   1.0000
  16.750   1.2626   0.09422   0.08763  -0.0271   0.0415   1.0000
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