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FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il)
Reynolds number: 500,000
Max Cl/Cd: 126.26 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx67k150-il-500000.txt
Download as CSV file: xf-fx67k150-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 67-K-150/17 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.1266   0.03100   0.02748  -0.1079   0.7330   0.0135
  -6.750  -0.1249   0.02723   0.02355  -0.1071   0.7311   0.0138
  -6.500  -0.1166   0.02427   0.02046  -0.1066   0.7294   0.0142
  -6.250  -0.1051   0.02171   0.01775  -0.1061   0.7278   0.0147
  -6.000  -0.0916   0.01929   0.01513  -0.1055   0.7264   0.0154
  -5.750  -0.0760   0.01700   0.01265  -0.1049   0.7245   0.0164
  -5.500  -0.0579   0.01488   0.01031  -0.1042   0.7225   0.0178
  -5.250  -0.0289   0.01545   0.01066  -0.1033   0.7203   0.0210
  -4.750   0.0032   0.00902   0.00351  -0.1022   0.7171   0.0237
  -4.500   0.0272   0.00819   0.00261  -0.1024   0.7155   0.0265
  -4.250   0.0605   0.01774   0.01133  -0.1056   0.7170   0.0159
  -4.000   0.0879   0.01606   0.00936  -0.1048   0.7155   0.0138
  -3.750   0.1139   0.01491   0.00809  -0.1044   0.7141   0.0138
  -3.500   0.1385   0.01387   0.00694  -0.1039   0.7127   0.0146
  -3.250   0.1634   0.01329   0.00637  -0.1036   0.7107   0.0168
  -3.000   0.1894   0.01288   0.00592  -0.1035   0.7086   0.0203
  -2.750   0.2148   0.01229   0.00529  -0.1033   0.7065   0.0291
  -2.500   0.2418   0.01195   0.00488  -0.1034   0.7046   0.0360
  -2.250   0.2694   0.01167   0.00456  -0.1035   0.7030   0.0478
  -2.000   0.2892   0.01005   0.00418  -0.1033   0.7015   0.4111
  -1.750   0.3102   0.00919   0.00416  -0.1025   0.7001   0.6694
  -1.500   0.3355   0.00920   0.00433  -0.1019   0.6984   0.7445
  -1.250   0.3608   0.00934   0.00453  -0.1014   0.6960   0.7882
  -1.000   0.3860   0.00949   0.00470  -0.1006   0.6938   0.8150
  -0.750   0.4123   0.00960   0.00478  -0.1003   0.6919   0.8300
  -0.500   0.4376   0.00969   0.00487  -0.0996   0.6902   0.8450
  -0.250   0.4647   0.00971   0.00485  -0.0994   0.6887   0.8526
   0.000   0.4931   0.00974   0.00480  -0.0997   0.6872   0.8592
   0.250   0.5201   0.00980   0.00484  -0.0997   0.6855   0.8647
   0.500   0.5467   0.00987   0.00492  -0.0997   0.6832   0.8710
   0.750   0.5728   0.00990   0.00496  -0.0996   0.6809   0.8759
   1.000   0.5999   0.00992   0.00497  -0.0997   0.6787   0.8813
   1.250   0.6280   0.00993   0.00496  -0.1000   0.6769   0.8864
   1.500   0.6553   0.00992   0.00493  -0.1001   0.6753   0.8908
   1.750   0.6837   0.00993   0.00492  -0.1004   0.6738   0.8955
   2.000   0.7115   0.01001   0.00498  -0.1007   0.6719   0.9000
   2.250   0.7364   0.01005   0.00509  -0.1005   0.6693   0.9041
   2.500   0.7628   0.01009   0.00516  -0.1005   0.6668   0.9087
   2.750   0.7906   0.01011   0.00518  -0.1009   0.6646   0.9132
   3.000   0.8178   0.01007   0.00517  -0.1009   0.6626   0.9171
   3.250   0.8460   0.01006   0.00515  -0.1013   0.6608   0.9215
   3.500   0.8737   0.01013   0.00522  -0.1016   0.6587   0.9262
   3.750   0.8975   0.01017   0.00535  -0.1012   0.6556   0.9310
   4.000   0.9232   0.01018   0.00544  -0.1011   0.6527   0.9363
   4.250   0.9507   0.01016   0.00545  -0.1013   0.6502   0.9415
   4.500   0.9799   0.01001   0.00527  -0.1017   0.6469   0.9463
   4.750   1.0037   0.00997   0.00533  -0.1013   0.6418   0.9536
   5.000   1.0319   0.00988   0.00531  -0.1016   0.6374   0.9599
   5.250   1.0631   0.00981   0.00525  -0.1026   0.6340   0.9665
   5.500   1.0950   0.00985   0.00538  -0.1040   0.6295   0.9737
   5.750   1.1290   0.00970   0.00528  -0.1057   0.6219   0.9817
   6.250   1.1865   0.00950   0.00518  -0.1070   0.5960   1.0000
   6.500   1.2058   0.00955   0.00517  -0.1058   0.5681   1.0000
   6.750   1.2202   0.00992   0.00539  -0.1039   0.5286   1.0000
   7.000   1.2125   0.01103   0.00612  -0.0982   0.4594   1.0000
   7.250   1.1876   0.01255   0.00733  -0.0899   0.4065   1.0000
   7.500   1.1667   0.01464   0.00918  -0.0838   0.3608   1.0000
   7.750   1.1431   0.01726   0.01147  -0.0780   0.3035   1.0000
   8.000   1.1221   0.01992   0.01379  -0.0728   0.2435   1.0000
   8.250   1.1089   0.02229   0.01585  -0.0687   0.1906   1.0000
   8.500   1.0804   0.02571   0.01874  -0.0634   0.1032   1.0000
   8.750   1.0618   0.02872   0.02132  -0.0593   0.0326   1.0000
   9.000   1.0636   0.03052   0.02301  -0.0573   0.0095   1.0000
   9.250   1.0743   0.03175   0.02430  -0.0561   0.0079   1.0000
   9.500   1.0851   0.03301   0.02566  -0.0550   0.0072   1.0000
   9.750   1.0938   0.03447   0.02721  -0.0537   0.0065   1.0000
  10.000   1.1032   0.03590   0.02873  -0.0525   0.0063   1.0000
  10.250   1.1110   0.03750   0.03042  -0.0513   0.0062   1.0000
  10.500   1.1153   0.03944   0.03247  -0.0499   0.0060   1.0000
  10.750   1.1215   0.04126   0.03437  -0.0487   0.0061   1.0000
  11.000   1.1246   0.04339   0.03660  -0.0474   0.0060   1.0000
  11.250   1.1279   0.04557   0.03888  -0.0461   0.0060   1.0000
  11.500   1.1331   0.04760   0.04099  -0.0451   0.0060   1.0000
  11.750   1.1351   0.04996   0.04344  -0.0438   0.0060   1.0000
  12.000   1.1360   0.05241   0.04599  -0.0424   0.0058   1.0000
  12.250   1.1417   0.05441   0.04806  -0.0411   0.0057   1.0000
  12.500   1.1544   0.05590   0.04964  -0.0409   0.0053   1.0000
  12.750   1.1635   0.05765   0.05150  -0.0400   0.0052   1.0000
  13.000   1.1739   0.05929   0.05324  -0.0390   0.0051   1.0000
  13.250   1.1877   0.06066   0.05471  -0.0378   0.0053   1.0000
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