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GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 797 AIRFOIL (goe797-il)
Reynolds number: 50,000
Max Cl/Cd: 20.93 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe797-il-50000-n5.txt
Download as CSV file: xf-goe797-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 797 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3160   0.13706   0.12963  -0.0447   1.0000   0.1114
 -10.750  -0.3108   0.13454   0.12717  -0.0424   1.0000   0.1086
 -10.250  -0.3613   0.12753   0.12032  -0.0435   0.9995   0.0967
 -10.000  -0.3427   0.12337   0.11612  -0.0463   0.9949   0.0959
  -9.750  -0.3316   0.11890   0.11162  -0.0501   0.9894   0.0956
  -9.500  -0.3257   0.11401   0.10672  -0.0548   0.9836   0.0959
  -9.250  -0.3229   0.10908   0.10178  -0.0593   0.9765   0.0962
  -9.000  -0.3182   0.10391   0.09659  -0.0643   0.9706   0.0963
  -8.750  -0.3168   0.09933   0.09200  -0.0677   0.9621   0.0962
  -8.500  -0.3165   0.09455   0.08721  -0.0715   0.9542   0.0960
  -8.250  -0.3213   0.08909   0.08173  -0.0764   0.9457   0.0959
  -8.000  -0.3348   0.08233   0.07490  -0.0819   0.9341   0.0962
  -7.750  -0.3539   0.07461   0.06696  -0.0870   0.9230   0.0967
  -7.500  -0.3361   0.07236   0.06471  -0.0883   0.9173   0.0984
  -7.250  -0.3282   0.06989   0.06217  -0.0887   0.9096   0.0997
  -7.000  -0.3216   0.06601   0.05812  -0.0906   0.9023   0.1010
  -6.750  -0.3148   0.06192   0.05377  -0.0924   0.8955   0.1023
  -6.500  -0.3087   0.05870   0.05031  -0.0927   0.8874   0.1043
  -6.000  -0.2874   0.05128   0.04194  -0.0946   0.8743   0.1104
  -5.750  -0.2680   0.04802   0.03814  -0.0958   0.8690   0.1133
  -5.500  -0.2372   0.04694   0.03704  -0.0973   0.8655   0.1168
  -5.250  -0.2259   0.04609   0.03605  -0.0955   0.8577   0.1200
  -5.000  -0.2023   0.04429   0.03385  -0.0960   0.8526   0.1246
  -4.750  -0.1714   0.04235   0.03141  -0.0977   0.8491   0.1301
  -4.500  -0.1536   0.04189   0.03095  -0.0966   0.8427   0.1341
  -4.250  -0.1315   0.04105   0.02990  -0.0963   0.8369   0.1394
  -4.000  -0.1001   0.03988   0.02836  -0.0975   0.8333   0.1464
  -3.500  -0.0561   0.03891   0.02709  -0.0965   0.8220   0.1593
  -3.250  -0.0273   0.03837   0.02656  -0.0970   0.8177   0.1666
  -3.000   0.0076   0.03769   0.02561  -0.0984   0.8147   0.1768
  -2.750   0.0217   0.03772   0.02574  -0.0967   0.8076   0.1831
  -2.500   0.0474   0.03748   0.02530  -0.0966   0.8024   0.1932
  -2.250   0.0804   0.03706   0.02494  -0.0976   0.7990   0.2040
  -2.000   0.1082   0.03685   0.02467  -0.0978   0.7947   0.2148
  -1.750   0.1222   0.03713   0.02492  -0.0960   0.7870   0.2242
  -1.500   0.1544   0.03687   0.02465  -0.0968   0.7831   0.2375
  -1.250   0.1913   0.03648   0.02422  -0.0983   0.7803   0.2527
  -1.000   0.1990   0.03710   0.02483  -0.0957   0.7712   0.2639
  -0.750   0.2297   0.03690   0.02467  -0.0962   0.7667   0.2827
  -0.500   0.2663   0.03643   0.02430  -0.0976   0.7637   0.3070
  -0.250   0.2750   0.03699   0.02501  -0.0952   0.7543   0.3287
   0.000   0.3058   0.03654   0.02486  -0.0958   0.7495   0.3804
   0.250   0.3411   0.03529   0.02443  -0.0963   0.7463   0.5303
   0.500   0.3507   0.03510   0.02529  -0.0919   0.7356   0.8704
   0.750   0.3992   0.03457   0.02446  -0.0948   0.7304   1.0000
   1.000   0.4128   0.03516   0.02486  -0.0927   0.7197   1.0000
   1.250   0.4476   0.03493   0.02440  -0.0934   0.7138   1.0000
   1.500   0.4819   0.03476   0.02403  -0.0940   0.7084   1.0000
   1.750   0.4921   0.03557   0.02473  -0.0916   0.6976   1.0000
   2.000   0.5316   0.03520   0.02419  -0.0929   0.6937   1.0000
   2.250   0.5353   0.03636   0.02530  -0.0898   0.6816   1.0000
   2.500   0.5714   0.03608   0.02488  -0.0906   0.6769   1.0000
   3.000   0.6124   0.03693   0.02558  -0.0884   0.6599   1.0000
   3.500   0.6540   0.03776   0.02628  -0.0863   0.6427   1.0000
   3.750   0.6917   0.03730   0.02574  -0.0871   0.6384   1.0000
   4.000   0.6960   0.03855   0.02698  -0.0843   0.6253   1.0000
   4.250   0.7363   0.03789   0.02626  -0.0853   0.6216   1.0000
   4.500   0.7384   0.03930   0.02767  -0.0823   0.6077   1.0000
   5.000   0.7810   0.04000   0.02833  -0.0804   0.5900   1.0000
   5.250   0.7876   0.04136   0.02971  -0.0782   0.5771   1.0000
   5.500   0.8227   0.04082   0.02914  -0.0785   0.5725   1.0000
   5.750   0.8273   0.04238   0.03072  -0.0762   0.5593   1.0000
   6.000   0.8642   0.04166   0.02998  -0.0765   0.5552   1.0000
   6.250   0.8667   0.04344   0.03179  -0.0743   0.5417   1.0000
   6.500   0.8941   0.04342   0.03176  -0.0739   0.5356   1.0000
   6.750   0.9032   0.04487   0.03324  -0.0723   0.5247   1.0000
   7.000   0.9339   0.04462   0.03299  -0.0721   0.5198   1.0000
   7.250   0.9371   0.04660   0.03502  -0.0702   0.5081   1.0000
   7.500   0.9658   0.04648   0.03491  -0.0699   0.5030   1.0000
   8.000   1.0037   0.04798   0.03647  -0.0682   0.4888   1.0000
   8.500   1.0282   0.05075   0.03935  -0.0660   0.4729   1.0000
   9.000   1.0555   0.05305   0.04174  -0.0637   0.4567   1.0000
   9.500   1.0928   0.05393   0.04269  -0.0615   0.4400   1.0000
   9.750   1.0806   0.05762   0.04647  -0.0596   0.4274   1.0000
  10.000   1.1261   0.05527   0.04412  -0.0593   0.4233   1.0000
  10.250   1.1051   0.06014   0.04912  -0.0575   0.4111   1.0000
  10.500   1.1469   0.05820   0.04720  -0.0571   0.4071   1.0000
  10.750   1.1230   0.06355   0.05267  -0.0554   0.3949   1.0000
  11.000   1.1656   0.06135   0.05050  -0.0548   0.3906   1.0000
  11.250   1.1386   0.06720   0.05648  -0.0534   0.3784   1.0000
  11.500   1.1812   0.06487   0.05419  -0.0527   0.3740   1.0000
  11.750   1.1514   0.07119   0.06065  -0.0515   0.3614   1.0000
  12.000   1.1960   0.06845   0.05794  -0.0506   0.3570   1.0000
  12.500   1.2082   0.07234   0.06201  -0.0487   0.3397   1.0000
  12.750   1.1690   0.08017   0.06998  -0.0482   0.3258   1.0000
  13.000   1.2198   0.07627   0.06610  -0.0469   0.3220   1.0000
  13.250   1.1744   0.08515   0.07514  -0.0469   0.3076   1.0000
  13.500   1.2265   0.08089   0.07090  -0.0453   0.3043   1.0000
  13.750   1.1741   0.09116   0.08131  -0.0461   0.2894   1.0000
  14.250   1.1091   0.10805   0.09837  -0.0491   0.2630   1.0000
  14.500   1.1270   0.10829   0.09868  -0.0483   0.2576   1.0000
  14.750   1.1637   0.10538   0.09585  -0.0464   0.2551   1.0000
  15.000   1.1171   0.11702   0.10757  -0.0498   0.2414   1.0000
  15.500   1.1080   0.12602   0.11670  -0.0521   0.2261   1.0000
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