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GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 647 AIRFOIL (goe647-il)
Reynolds number: 100,000
Max Cl/Cd: 41.51 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe647-il-100000.txt
Download as CSV file: xf-goe647-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 647 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1132   0.09944   0.09539  -0.0542   0.9613   0.1578
  -8.750  -0.0806   0.09513   0.09106  -0.0571   0.9562   0.1630
  -8.500  -0.1298   0.09285   0.08884  -0.0659   0.9437   0.1708
  -8.250  -0.0606   0.08633   0.08225  -0.0651   0.9418   0.1743
  -8.000  -0.0330   0.08201   0.07790  -0.0696   0.9380   0.1829
  -7.750  -0.1500   0.09027   0.08604  -0.0582   0.9547   0.1758
  -7.000  -0.2191   0.06025   0.05557  -0.0922   0.9067   0.1274
  -6.750  -0.2307   0.05060   0.04544  -0.0950   0.8934   0.1090
  -6.500  -0.2257   0.04114   0.03475  -0.0991   0.8866   0.1017
  -6.250  -0.2169   0.03857   0.03153  -0.0971   0.8732   0.1005
  -6.000  -0.1741   0.03528   0.02783  -0.1004   0.8693   0.1010
  -5.750  -0.1546   0.03372   0.02612  -0.0993   0.8572   0.1025
  -5.500  -0.1088   0.03171   0.02395  -0.1022   0.8521   0.1063
  -5.250  -0.0845   0.03034   0.02230  -0.1013   0.8406   0.1089
  -5.000  -0.0419   0.02849   0.02000  -0.1030   0.8342   0.1120
  -4.750  -0.0157   0.02709   0.01860  -0.1024   0.8233   0.1156
  -4.500   0.0238   0.02576   0.01718  -0.1037   0.8160   0.1232
  -4.250   0.0487   0.02479   0.01620  -0.1027   0.8050   0.1300
  -4.000   0.0855   0.02358   0.01495  -0.1034   0.7973   0.1415
  -3.750   0.1077   0.02298   0.01444  -0.1020   0.7855   0.1563
  -3.500   0.1431   0.02207   0.01364  -0.1025   0.7778   0.1875
  -3.250   0.1621   0.02174   0.01351  -0.1005   0.7652   0.2265
  -3.000   0.1938   0.02117   0.01307  -0.1003   0.7570   0.2857
  -2.750   0.2146   0.02108   0.01304  -0.0986   0.7443   0.3256
  -2.500   0.2387   0.02100   0.01297  -0.0972   0.7329   0.3589
  -2.250   0.2696   0.02076   0.01264  -0.0969   0.7232   0.3915
  -2.000   0.2910   0.02071   0.01264  -0.0952   0.7100   0.4149
  -1.750   0.3181   0.02051   0.01238  -0.0944   0.6987   0.4385
  -1.500   0.3475   0.02019   0.01198  -0.0939   0.6875   0.4618
  -1.250   0.3703   0.02005   0.01180  -0.0925   0.6739   0.4851
  -1.000   0.3963   0.01975   0.01155  -0.0916   0.6616   0.5115
  -0.750   0.4264   0.01934   0.01110  -0.0913   0.6502   0.5446
  -0.500   0.4485   0.01912   0.01098  -0.0898   0.6358   0.5796
  -0.250   0.4735   0.01881   0.01084  -0.0887   0.6221   0.6262
   0.000   0.5017   0.01836   0.01063  -0.0879   0.6093   0.7067
   0.250   0.6226   0.01780   0.01031  -0.1051   0.5862   1.0000
   0.500   0.6453   0.01799   0.01018  -0.1042   0.5735   1.0000
   0.750   0.6684   0.01818   0.01010  -0.1031   0.5607   1.0000
   1.000   0.6873   0.01848   0.01024  -0.1014   0.5471   1.0000
   1.250   0.7091   0.01877   0.01032  -0.1002   0.5352   1.0000
   1.500   0.7340   0.01901   0.01032  -0.0994   0.5246   1.0000
   1.750   0.7526   0.01938   0.01061  -0.0977   0.5128   1.0000
   2.000   0.7773   0.01969   0.01069  -0.0969   0.5034   1.0000
   2.250   0.7976   0.02004   0.01095  -0.0955   0.4929   1.0000
   2.500   0.8206   0.02043   0.01118  -0.0945   0.4841   1.0000
   2.750   0.8425   0.02081   0.01146  -0.0933   0.4752   1.0000
   3.000   0.8669   0.02124   0.01174  -0.0927   0.4678   1.0000
   3.250   0.8868   0.02171   0.01219  -0.0913   0.4597   1.0000
   3.500   0.9156   0.02209   0.01233  -0.0913   0.4534   1.0000
   3.750   0.9318   0.02268   0.01298  -0.0894   0.4457   1.0000
   4.000   0.9562   0.02309   0.01328  -0.0888   0.4391   1.0000
   4.250   0.9809   0.02363   0.01372  -0.0883   0.4334   1.0000
   4.500   0.9982   0.02427   0.01441  -0.0866   0.4270   1.0000
   4.750   1.0233   0.02476   0.01481  -0.0861   0.4217   1.0000
   5.000   1.0506   0.02538   0.01529  -0.0861   0.4172   1.0000
   5.250   1.0643   0.02617   0.01623  -0.0840   0.4117   1.0000
   5.500   1.0855   0.02678   0.01683  -0.0830   0.4067   1.0000
   5.750   1.1144   0.02729   0.01720  -0.0832   0.4024   1.0000
   6.000   1.1317   0.02815   0.01813  -0.0818   0.3979   1.0000
   6.250   1.1456   0.02904   0.01914  -0.0798   0.3932   1.0000
   6.500   1.1662   0.02979   0.01990  -0.0789   0.3892   1.0000
   6.750   1.1930   0.03044   0.02048  -0.0789   0.3857   1.0000
   7.000   1.2152   0.03142   0.02145  -0.0783   0.3825   1.0000
   7.250   1.2198   0.03273   0.02299  -0.0752   0.3788   1.0000
   7.500   1.2316   0.03385   0.02422  -0.0731   0.3750   1.0000
   7.750   1.2508   0.03470   0.02509  -0.0721   0.3714   1.0000
   8.000   1.2782   0.03539   0.02573  -0.0723   0.3683   1.0000
   8.250   1.2969   0.03662   0.02698  -0.0714   0.3655   1.0000
   8.500   1.2846   0.03870   0.02936  -0.0665   0.3625   1.0000
   8.750   1.2740   0.04086   0.03174  -0.0620   0.3595   1.0000
   9.000   1.2672   0.04292   0.03394  -0.0582   0.3567   1.0000
   9.250   1.2743   0.04441   0.03549  -0.0561   0.3542   1.0000
   9.500   1.3032   0.04516   0.03623  -0.0565   0.3516   1.0000
   9.750   1.3435   0.04591   0.03690  -0.0585   0.3491   1.0000
  10.750   0.6539   0.13633   0.12857  -0.0618   0.3749   1.0000
  11.000   0.6714   0.13849   0.13073  -0.0618   0.3706   1.0000
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