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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.32 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe199-il-1000000-n5.txt
Download as CSV file: xf-goe199-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 199 (L.F.G. 5406) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3473   0.09595   0.09430  -0.0188   0.9260   0.0061
  -8.250  -0.3466   0.09223   0.09050  -0.0201   0.9007   0.0063
  -8.000  -0.3482   0.08750   0.08569  -0.0227   0.8795   0.0066
  -7.750  -0.3380   0.08393   0.08206  -0.0262   0.8639   0.0068
  -7.500  -0.3243   0.08100   0.07906  -0.0293   0.8504   0.0069
  -7.250  -0.3090   0.07792   0.07593  -0.0328   0.8390   0.0071
  -7.000  -0.2921   0.07485   0.07280  -0.0363   0.8288   0.0073
  -6.750  -0.2736   0.07141   0.06931  -0.0403   0.8195   0.0078
  -6.500  -0.2533   0.06585   0.06366  -0.0465   0.8101   0.0085
  -6.250  -0.2300   0.06088   0.05860  -0.0521   0.8015   0.0090
  -6.000  -0.2062   0.05821   0.05586  -0.0552   0.7941   0.0092
  -5.750  -0.1812   0.05537   0.05295  -0.0585   0.7879   0.0095
  -5.500  -0.1547   0.05212   0.04961  -0.0620   0.7816   0.0101
  -5.250  -0.1220   0.04562   0.04294  -0.0682   0.7763   0.0115
  -5.000  -0.0949   0.04351   0.04075  -0.0702   0.7699   0.0117
  -4.500  -0.0383   0.03879   0.03582  -0.0743   0.7589   0.0126
  -4.250  -0.0021   0.03282   0.02956  -0.0780   0.7534   0.0144
  -4.000   0.0253   0.03146   0.02810  -0.0790   0.7473   0.0146
  -3.750   0.0536   0.02986   0.02640  -0.0800   0.7385   0.0149
  -3.500   0.0826   0.02804   0.02439  -0.0809   0.7230   0.0155
  -3.250   0.1191   0.02239   0.01823  -0.0822   0.7068   0.0175
  -3.000   0.1469   0.02106   0.01666  -0.0827   0.6806   0.0178
  -2.750   0.1747   0.02036   0.01579  -0.0831   0.6553   0.0180
  -2.500   0.2027   0.01967   0.01494  -0.0835   0.6315   0.0184
  -2.250   0.2317   0.01849   0.01352  -0.0838   0.6075   0.0190
  -2.000   0.2612   0.01702   0.01174  -0.0841   0.5790   0.0195
  -1.750   0.2907   0.01558   0.00994  -0.0843   0.5504   0.0199
  -1.500   0.3203   0.01405   0.00805  -0.0844   0.5277   0.0206
  -1.250   0.3494   0.01318   0.00687  -0.0845   0.5097   0.0210
  -1.000   0.3780   0.01233   0.00580  -0.0847   0.4951   0.0215
  -0.750   0.4064   0.01188   0.00523  -0.0849   0.4811   0.0217
  -0.500   0.4348   0.01161   0.00487  -0.0851   0.4663   0.0220
  -0.250   0.4631   0.01136   0.00451  -0.0852   0.4502   0.0222
   0.000   0.4914   0.01115   0.00420  -0.0854   0.4313   0.0225
   0.250   0.5194   0.01098   0.00391  -0.0855   0.4090   0.0227
   0.500   0.5474   0.01087   0.00366  -0.0856   0.3826   0.0229
   0.750   0.5752   0.01085   0.00351  -0.0857   0.3563   0.0233
   1.000   0.6030   0.01080   0.00334  -0.0858   0.3326   0.0235
   1.250   0.6308   0.01074   0.00318  -0.0859   0.3118   0.0236
   1.500   0.6586   0.01072   0.00307  -0.0860   0.2927   0.0238
   1.750   0.6865   0.01073   0.00299  -0.0861   0.2758   0.0242
   2.000   0.7144   0.01076   0.00295  -0.0862   0.2620   0.0247
   2.250   0.7423   0.01081   0.00295  -0.0863   0.2502   0.0252
   2.500   0.7700   0.01089   0.00298  -0.0864   0.2376   0.0256
   2.750   0.7977   0.01100   0.00303  -0.0865   0.2261   0.0259
   3.000   0.8256   0.01101   0.00301  -0.0867   0.2180   0.0264
   3.250   0.8534   0.01107   0.00304  -0.0868   0.2120   0.0272
   3.500   0.8813   0.01113   0.00311  -0.0869   0.2073   0.0282
   3.750   0.9090   0.01122   0.00319  -0.0870   0.2024   0.0288
   4.000   0.9366   0.01132   0.00328  -0.0871   0.1979   0.0294
   4.250   0.9644   0.01141   0.00338  -0.0872   0.1950   0.0305
   4.500   0.9920   0.01151   0.00348  -0.0872   0.1918   0.0316
   4.750   1.0194   0.01163   0.00361  -0.0873   0.1885   0.0338
   5.000   1.0467   0.01178   0.00377  -0.0874   0.1841   0.0389
   5.250   1.0713   0.01038   0.00410  -0.0873   0.1806   1.0000
   5.500   1.0985   0.01055   0.00426  -0.0873   0.1762   1.0000
   5.750   1.1255   0.01074   0.00444  -0.0874   0.1727   1.0000
   6.000   1.1524   0.01095   0.00463  -0.0874   0.1691   1.0000
   6.250   1.1794   0.01112   0.00481  -0.0874   0.1655   1.0000
   6.500   1.2059   0.01135   0.00501  -0.0874   0.1592   1.0000
   6.750   1.2322   0.01159   0.00524  -0.0873   0.1530   1.0000
   7.000   1.2583   0.01185   0.00547  -0.0872   0.1441   1.0000
   7.250   1.2818   0.01244   0.00586  -0.0868   0.1115   1.0000
   7.500   1.3021   0.01346   0.00666  -0.0860   0.0695   1.0000
   7.750   1.3229   0.01437   0.00737  -0.0852   0.0359   1.0000
   8.000   1.3468   0.01483   0.00782  -0.0848   0.0286   1.0000
   8.250   1.3706   0.01527   0.00826  -0.0843   0.0238   1.0000
   8.500   1.3942   0.01571   0.00871  -0.0839   0.0196   1.0000
   8.750   1.4172   0.01620   0.00918  -0.0834   0.0159   1.0000
   9.000   1.4403   0.01664   0.00964  -0.0829   0.0138   1.0000
   9.250   1.4625   0.01715   0.01016  -0.0822   0.0118   1.0000
   9.500   1.4849   0.01762   0.01067  -0.0816   0.0105   1.0000
   9.750   1.5066   0.01811   0.01119  -0.0809   0.0096   1.0000
  10.000   1.5274   0.01867   0.01178  -0.0801   0.0086   1.0000
  10.250   1.5474   0.01927   0.01242  -0.0791   0.0079   1.0000
  10.500   1.5674   0.01981   0.01302  -0.0781   0.0075   1.0000
  10.750   1.5864   0.02039   0.01366  -0.0770   0.0070   1.0000
  11.000   1.6041   0.02102   0.01433  -0.0757   0.0065   1.0000
  11.250   1.6200   0.02173   0.01508  -0.0742   0.0060   1.0000
  11.500   1.6335   0.02255   0.01596  -0.0722   0.0056   1.0000
  11.750   1.6473   0.02326   0.01675  -0.0704   0.0054   1.0000
  12.000   1.6563   0.02406   0.01763  -0.0677   0.0052   1.0000
  12.250   1.6646   0.02497   0.01862  -0.0651   0.0050   1.0000
  12.500   1.6726   0.02599   0.01972  -0.0627   0.0048   1.0000
  12.750   1.6804   0.02713   0.02093  -0.0605   0.0046   1.0000
  13.000   1.6872   0.02841   0.02230  -0.0585   0.0045   1.0000
  13.250   1.6932   0.02985   0.02382  -0.0566   0.0043   1.0000
  13.500   1.6976   0.03150   0.02556  -0.0548   0.0042   1.0000
  13.750   1.6998   0.03346   0.02761  -0.0531   0.0040   1.0000
  14.000   1.6990   0.03583   0.03009  -0.0516   0.0039   1.0000
  14.250   1.6987   0.03827   0.03265  -0.0504   0.0038   1.0000
  14.500   1.6991   0.04077   0.03525  -0.0494   0.0037   1.0000
  14.750   1.6979   0.04354   0.03814  -0.0487   0.0037   1.0000
  15.000   1.6948   0.04665   0.04137  -0.0482   0.0036   1.0000
  15.250   1.6901   0.05010   0.04494  -0.0480   0.0036   1.0000
  15.500   1.6835   0.05395   0.04891  -0.0481   0.0035   1.0000
  15.750   1.6751   0.05819   0.05328  -0.0485   0.0034   1.0000
  16.000   1.6646   0.06301   0.05823  -0.0493   0.0034   1.0000
  16.250   1.6526   0.06833   0.06368  -0.0506   0.0033   1.0000
  16.500   1.6385   0.07409   0.06958  -0.0522   0.0033   1.0000
  16.750   1.6224   0.08034   0.07596  -0.0541   0.0033   1.0000
  17.000   1.6041   0.08709   0.08285  -0.0562   0.0033   1.0000
  17.250   1.5843   0.09414   0.09004  -0.0586   0.0032   1.0000
  17.500   1.5643   0.10138   0.09741  -0.0611   0.0032   1.0000
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