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GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 483 AIRFOIL (goe483-il)
Reynolds number: 200,000
Max Cl/Cd: 83.76 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe483-il-200000.txt
Download as CSV file: xf-goe483-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 483 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.3117   0.08802   0.08509  -0.0230   1.0000   0.0279
  -6.250  -0.3198   0.08603   0.08315  -0.0191   1.0000   0.0283
  -6.000  -0.3106   0.08295   0.08010  -0.0197   0.9980   0.0291
  -5.750  -0.2808   0.07859   0.07571  -0.0258   0.9931   0.0304
  -5.500  -0.2490   0.07432   0.07140  -0.0329   0.9871   0.0321
  -5.250  -0.2109   0.06983   0.06685  -0.0416   0.9827   0.0343
  -5.000  -0.1697   0.06577   0.06272  -0.0514   0.9751   0.0372
  -4.750  -0.1021   0.06185   0.05858  -0.0675   0.9704   0.0387
  -4.500  -0.0765   0.05551   0.05220  -0.0723   0.9643   0.0397
  -4.250  -0.0520   0.05191   0.04861  -0.0741   0.9595   0.0418
  -4.000   0.0536   0.02716   0.02377  -0.0895   0.9416   0.0521
  -3.750   0.0502   0.04330   0.03957  -0.0916   0.9504   0.0523
  -3.500   0.0730   0.04077   0.03710  -0.0922   0.9450   0.0573
  -3.250   0.1288   0.03628   0.03227  -0.1005   0.9413   0.0657
  -3.000   0.1532   0.03402   0.02997  -0.1011   0.9324   0.0686
  -2.750   0.1996   0.03045   0.02601  -0.1059   0.9274   0.0789
  -2.500   0.2357   0.02260   0.01754  -0.1079   0.9186   0.0457
  -2.250   0.2713   0.01854   0.01275  -0.1092   0.9125   0.0479
  -2.000   0.3004   0.01597   0.00952  -0.1088   0.9029   0.0488
  -1.750   0.3289   0.01436   0.00749  -0.1083   0.8937   0.0536
  -1.500   0.3572   0.01374   0.00672  -0.1078   0.8847   0.0629
  -1.250   0.3833   0.01301   0.00589  -0.1069   0.8736   0.0727
  -1.000   0.4092   0.01258   0.00539  -0.1060   0.8622   0.0858
  -0.750   0.4353   0.01221   0.00492  -0.1051   0.8510   0.1042
  -0.500   0.4610   0.01178   0.00454  -0.1042   0.8397   0.1338
  -0.250   0.4871   0.01167   0.00439  -0.1034   0.8281   0.1600
   0.250   0.5388   0.01166   0.00430  -0.1018   0.8024   0.2025
   0.500   0.5644   0.01158   0.00422  -0.1011   0.7885   0.2217
   0.750   0.5902   0.01145   0.00404  -0.1003   0.7742   0.2420
   1.000   0.6156   0.01127   0.00390  -0.0995   0.7588   0.2642
   1.250   0.6409   0.01108   0.00375  -0.0988   0.7422   0.2885
   1.500   0.6661   0.01089   0.00361  -0.0981   0.7251   0.3161
   1.750   0.6913   0.01069   0.00349  -0.0973   0.7080   0.3553
   2.000   0.7217   0.00949   0.00338  -0.0976   0.6909   1.0000
   2.250   0.7476   0.00961   0.00336  -0.0969   0.6716   1.0000
   2.500   0.7733   0.00975   0.00336  -0.0963   0.6531   1.0000
   2.750   0.7990   0.00992   0.00339  -0.0956   0.6353   1.0000
   3.000   0.8246   0.01010   0.00348  -0.0950   0.6164   1.0000
   3.250   0.8500   0.01032   0.00361  -0.0944   0.5982   1.0000
   3.500   0.8753   0.01057   0.00375  -0.0938   0.5809   1.0000
   3.750   0.9006   0.01084   0.00393  -0.0932   0.5637   1.0000
   4.000   0.9259   0.01112   0.00416  -0.0927   0.5472   1.0000
   4.250   0.9512   0.01143   0.00442  -0.0921   0.5315   1.0000
   4.500   0.9764   0.01174   0.00475  -0.0916   0.5162   1.0000
   4.750   1.0016   0.01207   0.00507  -0.0911   0.5014   1.0000
   5.000   1.0265   0.01238   0.00538  -0.0905   0.4857   1.0000
   5.250   1.0496   0.01259   0.00557  -0.0896   0.4591   1.0000
   5.500   1.0728   0.01282   0.00581  -0.0887   0.4317   1.0000
   5.750   1.0964   0.01309   0.00610  -0.0879   0.4077   1.0000
   6.000   1.1178   0.01345   0.00634  -0.0867   0.3643   1.0000
   6.250   1.1362   0.01419   0.00675  -0.0853   0.2932   1.0000
   6.500   1.1457   0.01624   0.00780  -0.0829   0.1367   1.0000
   6.750   1.1539   0.01874   0.00957  -0.0804   0.0360   1.0000
   7.000   1.1724   0.01988   0.01085  -0.0789   0.0299   1.0000
   7.250   1.1907   0.02096   0.01218  -0.0773   0.0277   1.0000
   7.500   1.2062   0.02224   0.01363  -0.0754   0.0262   1.0000
   7.750   1.2192   0.02371   0.01523  -0.0732   0.0252   1.0000
   8.000   1.2306   0.02535   0.01696  -0.0708   0.0245   1.0000
   8.250   1.2407   0.02728   0.01892  -0.0685   0.0231   1.0000
   8.500   1.2531   0.03055   0.02220  -0.0665   0.0216   1.0000
   8.750   1.2772   0.03346   0.02519  -0.0658   0.0215   1.0000
   9.000   1.3012   0.03569   0.02760  -0.0651   0.0218   1.0000
   9.250   1.3229   0.03729   0.02938  -0.0639   0.0224   1.0000
   9.500   1.3452   0.03906   0.03159  -0.0619   0.0250   1.0000
  15.000   0.8849   0.17917   0.17645  -0.0933   0.0673   1.0000
  15.250   0.9015   0.18080   0.17812  -0.0914   0.0653   1.0000
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