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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 100,000
Max Cl/Cd: 60.15 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe517-il-100000-n5.txt
Download as CSV file: xf-goe517-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 517 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3162   0.09180   0.08739  -0.0272   1.0000   0.0403
  -7.000  -0.3255   0.09027   0.08596  -0.0253   1.0000   0.0409
  -6.750  -0.3333   0.08855   0.08434  -0.0240   1.0000   0.0415
  -6.500  -0.3412   0.08694   0.08282  -0.0227   1.0000   0.0420
  -6.250  -0.3127   0.08303   0.07885  -0.0346   0.9913   0.0445
  -6.000  -0.2754   0.07836   0.07405  -0.0467   0.9818   0.0451
  -5.750  -0.2462   0.07301   0.06863  -0.0535   0.9741   0.0455
  -5.500  -0.2337   0.06839   0.06407  -0.0520   0.9689   0.0472
  -5.000  -0.1726   0.05806   0.05344  -0.0636   0.9540   0.0340
  -4.750  -0.1455   0.05381   0.04909  -0.0673   0.9474   0.0306
  -4.500  -0.1136   0.04884   0.04392  -0.0723   0.9402   0.0281
  -4.250  -0.0755   0.04289   0.03764  -0.0778   0.9344   0.0259
  -4.000  -0.0437   0.03795   0.03234  -0.0808   0.9271   0.0253
  -3.750  -0.0121   0.03519   0.02934  -0.0830   0.9212   0.0275
  -3.250   0.0501   0.02707   0.02018  -0.0855   0.9078   0.0284
  -3.000   0.0848   0.02361   0.01602  -0.0867   0.9034   0.0303
  -2.750   0.1120   0.02129   0.01306  -0.0861   0.8950   0.0337
  -2.500   0.1459   0.01937   0.01071  -0.0868   0.8897   0.0369
  -2.250   0.1748   0.01852   0.00966  -0.0868   0.8816   0.0439
  -2.000   0.2070   0.01762   0.00864  -0.0873   0.8750   0.0542
  -1.750   0.2360   0.01704   0.00799  -0.0873   0.8668   0.0707
  -1.500   0.2674   0.01664   0.00751  -0.0877   0.8595   0.0963
  -1.250   0.2954   0.01636   0.00714  -0.0876   0.8502   0.1194
  -1.000   0.3271   0.01599   0.00666  -0.0881   0.8427   0.1393
  -0.750   0.3534   0.01568   0.00633  -0.0876   0.8321   0.1530
  -0.500   0.3830   0.01536   0.00596  -0.0876   0.8229   0.1673
  -0.250   0.4129   0.01506   0.00559  -0.0877   0.8122   0.1862
   0.000   0.4397   0.01478   0.00534  -0.0872   0.7984   0.2180
   0.250   0.4657   0.01420   0.00512  -0.0867   0.7835   0.3375
   0.500   0.5229   0.01271   0.00478  -0.0923   0.7678   1.0000
   0.750   0.5480   0.01276   0.00464  -0.0914   0.7518   1.0000
   1.000   0.5730   0.01284   0.00456  -0.0906   0.7367   1.0000
   1.250   0.5980   0.01292   0.00451  -0.0898   0.7215   1.0000
   1.500   0.6229   0.01302   0.00448  -0.0889   0.7061   1.0000
   1.750   0.6477   0.01312   0.00448  -0.0881   0.6903   1.0000
   2.000   0.6726   0.01323   0.00449  -0.0873   0.6745   1.0000
   2.250   0.6974   0.01336   0.00453  -0.0865   0.6586   1.0000
   2.500   0.7222   0.01351   0.00460  -0.0857   0.6426   1.0000
   2.750   0.7469   0.01367   0.00468  -0.0850   0.6269   1.0000
   3.000   0.7714   0.01386   0.00480  -0.0842   0.6112   1.0000
   3.250   0.7959   0.01406   0.00496  -0.0834   0.5958   1.0000
   3.500   0.8202   0.01429   0.00513  -0.0826   0.5805   1.0000
   3.750   0.8445   0.01455   0.00534  -0.0818   0.5654   1.0000
   4.000   0.8685   0.01482   0.00561  -0.0810   0.5505   1.0000
   4.250   0.8925   0.01512   0.00590  -0.0802   0.5355   1.0000
   4.500   0.9161   0.01543   0.00621  -0.0793   0.5202   1.0000
   4.750   0.9396   0.01576   0.00658  -0.0785   0.5047   1.0000
   5.000   0.9628   0.01609   0.00696  -0.0776   0.4888   1.0000
   5.250   0.9857   0.01643   0.00737  -0.0767   0.4722   1.0000
   5.500   1.0083   0.01678   0.00782  -0.0757   0.4549   1.0000
   5.750   1.0309   0.01714   0.00827  -0.0747   0.4381   1.0000
   6.000   1.0532   0.01751   0.00874  -0.0738   0.4217   1.0000
   6.250   1.0754   0.01792   0.00926  -0.0727   0.4061   1.0000
   6.500   1.0976   0.01836   0.00981  -0.0717   0.3920   1.0000
   6.750   1.1188   0.01882   0.01037  -0.0706   0.3763   1.0000
   7.000   1.1341   0.01938   0.01081  -0.0684   0.3419   1.0000
   7.250   1.1470   0.02014   0.01142  -0.0661   0.3019   1.0000
   7.500   1.1594   0.02098   0.01213  -0.0638   0.2505   1.0000
   7.750   1.1647   0.02251   0.01309  -0.0607   0.1450   1.0000
   8.000   1.1591   0.02545   0.01512  -0.0566   0.0463   1.0000
   8.250   1.1663   0.02717   0.01677  -0.0538   0.0320   1.0000
   8.500   1.1743   0.02867   0.01841  -0.0510   0.0274   1.0000
   8.750   1.1802   0.03007   0.02003  -0.0480   0.0250   1.0000
   9.000   1.1824   0.03162   0.02179  -0.0447   0.0226   1.0000
   9.250   1.1797   0.03354   0.02387  -0.0412   0.0209   1.0000
   9.500   1.1744   0.03575   0.02623  -0.0378   0.0198   1.0000
   9.750   1.1754   0.03765   0.02831  -0.0353   0.0192   1.0000
  10.000   1.1767   0.03971   0.03053  -0.0331   0.0185   1.0000
  10.250   1.1796   0.04183   0.03279  -0.0311   0.0178   1.0000
  10.500   1.1841   0.04395   0.03503  -0.0295   0.0168   1.0000
  10.750   1.1888   0.04617   0.03734  -0.0281   0.0157   1.0000
  11.000   1.1951   0.04864   0.03984  -0.0267   0.0149   1.0000
  11.250   1.2074   0.05120   0.04256  -0.0253   0.0144   1.0000
  11.500   1.2178   0.05381   0.04544  -0.0240   0.0141   1.0000
  11.750   1.2254   0.05682   0.04874  -0.0228   0.0138   1.0000
  12.000   1.2282   0.06005   0.05226  -0.0217   0.0136   1.0000
  12.250   1.2259   0.06351   0.05602  -0.0209   0.0133   1.0000
  12.500   1.2209   0.06724   0.06003  -0.0204   0.0131   1.0000
  12.750   1.2129   0.07128   0.06435  -0.0204   0.0129   1.0000
  13.000   1.2033   0.07564   0.06896  -0.0208   0.0128   1.0000
  13.250   1.1922   0.08024   0.07380  -0.0218   0.0125   1.0000
  13.500   1.1794   0.08537   0.07917  -0.0234   0.0124   1.0000
  13.750   1.1657   0.09086   0.08487  -0.0255   0.0123   1.0000
  14.000   1.1495   0.09722   0.09149  -0.0284   0.0126   1.0000
  14.250   1.1337   0.10378   0.09826  -0.0318   0.0126   1.0000
  14.500   1.1174   0.11091   0.10558  -0.0358   0.0127   1.0000
  14.750   1.1009   0.11863   0.11348  -0.0404   0.0128   1.0000
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