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GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 383 AIRFOIL (goe383-il)
Reynolds number: 100,000
Max Cl/Cd: 25 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe383-il-100000.txt
Download as CSV file: xf-goe383-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 383 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0314   0.10528   0.10023  -0.0912   0.9239   0.1656
 -10.000  -0.0753   0.10188   0.09687  -0.0981   0.9105   0.1734
  -9.750  -0.0409   0.09859   0.09354  -0.0960   0.9031   0.1750
  -9.500  -0.0210   0.09632   0.09126  -0.0949   0.8930   0.1777
  -9.250  -0.0891   0.09286   0.08784  -0.1035   0.8812   0.1888
  -9.000  -0.0429   0.09013   0.08509  -0.0990   0.8738   0.1904
  -8.750  -0.2625   0.05928   0.05329  -0.1165   0.8573   0.1111
  -8.500  -0.2535   0.05682   0.05077  -0.1156   0.8495   0.1095
  -8.250  -0.2486   0.05362   0.04739  -0.1146   0.8442   0.1080
  -8.000  -0.2960   0.04856   0.04135  -0.1086   0.8332   0.1017
  -7.750  -0.2865   0.04620   0.03866  -0.1069   0.8270   0.1009
  -7.500  -0.2674   0.04365   0.03584  -0.1062   0.8228   0.1004
  -7.250  -0.2629   0.04242   0.03441  -0.1034   0.8136   0.1000
  -7.000  -0.2465   0.04054   0.03224  -0.1020   0.8071   0.0998
  -6.750  -0.2227   0.03848   0.02982  -0.1013   0.8027   0.0999
  -6.500  -0.2082   0.03739   0.02846  -0.0995   0.7958   0.1002
  -6.250  -0.1939   0.03651   0.02732  -0.0975   0.7881   0.1009
  -6.000  -0.1659   0.03514   0.02583  -0.0974   0.7835   0.1027
  -5.750  -0.1336   0.03395   0.02461  -0.0977   0.7801   0.1053
  -5.500  -0.1241   0.03398   0.02458  -0.0953   0.7713   0.1070
  -5.250  -0.1004   0.03321   0.02364  -0.0944   0.7652   0.1092
  -5.000  -0.0684   0.03203   0.02236  -0.0946   0.7611   0.1118
  -4.750  -0.0341   0.03096   0.02131  -0.0950   0.7579   0.1155
  -4.500  -0.0292   0.03148   0.02184  -0.0921   0.7477   0.1182
  -4.250  -0.0014   0.03073   0.02112  -0.0917   0.7424   0.1238
  -4.000   0.0316   0.02986   0.02020  -0.0918   0.7385   0.1324
  -3.750   0.0556   0.02932   0.01980  -0.0910   0.7333   0.1419
  -3.500   0.0623   0.02962   0.02025  -0.0882   0.7235   0.1511
  -3.250   0.0890   0.02849   0.01937  -0.0875   0.7190   0.1833
  -3.000   0.1147   0.02702   0.01856  -0.0866   0.7155   0.2892
  -2.750   0.1164   0.02767   0.01951  -0.0833   0.7046   0.3456
  -2.500   0.1398   0.02706   0.01927  -0.0821   0.6990   0.4260
  -2.250   0.1687   0.02626   0.01887  -0.0812   0.6952   0.5216
  -2.000   0.1807   0.02665   0.01965  -0.0782   0.6877   0.6050
  -1.750   0.1922   0.02715   0.02039  -0.0750   0.6790   0.6791
  -1.500   0.2207   0.02685   0.02020  -0.0729   0.6750   0.7508
  -1.250   0.2526   0.02661   0.01997  -0.0709   0.6719   0.8106
  -1.000   0.2495   0.02815   0.02165  -0.0660   0.6592   0.8467
  -0.750   0.2880   0.02811   0.02150  -0.0655   0.6549   0.8878
  -0.500   0.3496   0.02794   0.02111  -0.0694   0.6518   0.9139
  -0.250   0.4016   0.02876   0.02182  -0.0736   0.6444   0.9362
   0.000   0.4818   0.02917   0.02206  -0.0828   0.6367   0.9568
   0.250   0.5677   0.02862   0.02127  -0.0924   0.6322   0.9735
   0.500   0.6387   0.02799   0.02038  -0.0999   0.6284   0.9851
   0.750   0.6831   0.02906   0.02150  -0.1053   0.6180   0.9990
   1.000   0.7009   0.02915   0.02149  -0.1044   0.6124   1.0000
   1.250   0.7225   0.02890   0.02110  -0.1035   0.6084   1.0000
   1.500   0.7081   0.03030   0.02257  -0.0983   0.6001   1.0000
   1.750   0.7007   0.03116   0.02342  -0.0936   0.5929   1.0000
   2.000   0.7191   0.03107   0.02322  -0.0921   0.5891   1.0000
   2.250   0.7470   0.03077   0.02278  -0.0918   0.5862   1.0000
   2.500   0.6444   0.03527   0.02748  -0.0749   0.5718   1.0000
   2.750   0.6816   0.03472   0.02681  -0.0757   0.5690   1.0000
   3.000   0.7233   0.03407   0.02603  -0.0771   0.5668   1.0000
   3.250   0.7676   0.03346   0.02527  -0.0789   0.5648   1.0000
   3.500   0.5847   0.04470   0.03678  -0.0572   0.5413   1.0000
   3.750   0.6510   0.04192   0.03387  -0.0595   0.5423   1.0000
   4.000   0.7311   0.03907   0.03088  -0.0643   0.5434   1.0000
   4.250   0.5262   0.05723   0.04932  -0.0508   0.5116   1.0000
   4.500   0.5662   0.05632   0.04832  -0.0509   0.5093   1.0000
   4.750   0.5317   0.06208   0.05412  -0.0489   0.4977   1.0000
   5.000   0.5565   0.06247   0.05445  -0.0486   0.4929   1.0000
   5.250   0.5973   0.06141   0.05332  -0.0486   0.4906   1.0000
   5.500   0.5639   0.06727   0.05922  -0.0470   0.4787   1.0000
   5.750   0.5911   0.06743   0.05934  -0.0467   0.4743   1.0000
   6.000   0.6320   0.06629   0.05813  -0.0467   0.4720   1.0000
   6.250   0.6764   0.06470   0.05648  -0.0466   0.4705   1.0000
   6.500   0.6274   0.07234   0.06419  -0.0451   0.4556   1.0000
   6.750   0.6688   0.07105   0.06285  -0.0449   0.4535   1.0000
   7.000   0.6320   0.07766   0.06952  -0.0439   0.4400   1.0000
   7.250   0.6663   0.07702   0.06885  -0.0436   0.4368   1.0000
   7.500   0.6498   0.08181   0.07367  -0.0430   0.4266   1.0000
   7.750   0.6666   0.08296   0.07481  -0.0426   0.4205   1.0000
   8.000   0.7042   0.08187   0.07368  -0.0421   0.4179   1.0000
   8.250   0.6719   0.08856   0.08043  -0.0418   0.4052   1.0000
   8.500   0.6982   0.08875   0.08061  -0.0414   0.4013   1.0000
   8.750   0.7360   0.08759   0.07942  -0.0409   0.3992   1.0000
   9.000   0.6942   0.09569   0.08759  -0.0411   0.3855   1.0000
   9.250   0.7251   0.09529   0.08716  -0.0406   0.3824   1.0000
   9.500   0.7013   0.10176   0.09368  -0.0410   0.3735   1.0000
   9.750   0.7011   0.10531   0.09727  -0.0412   0.3675   1.0000
  10.000   0.7303   0.10518   0.09713  -0.0407   0.3645   1.0000
  10.250   0.7681   0.10393   0.09585  -0.0400   0.3628   1.0000
  10.500   0.6942   0.11729   0.10933  -0.0424   0.3526   1.0000
  10.750   0.6965   0.12100   0.11307  -0.0430   0.3500   1.0000
  11.000   0.7177   0.12225   0.11432  -0.0429   0.3474   1.0000
  11.250   0.7648   0.12000   0.11205  -0.0417   0.3452   1.0000
  11.500   0.6794   0.13766   0.12987  -0.0471   0.3597   1.0000
  11.750   0.7117   0.14016   0.13238  -0.0476   0.3613   1.0000
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