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GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 549 AIRFOIL (goe549-il)
Reynolds number: 100,000
Max Cl/Cd: 43.04 at α=11.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe549-il-100000.txt
Download as CSV file: xf-goe549-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 549 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  -0.2541   0.11605   0.11128  -0.0448   1.0000   0.1029
 -10.000  -0.2793   0.11594   0.11134  -0.0472   1.0000   0.1043
  -9.750  -0.3062   0.11573   0.11131  -0.0475   1.0000   0.1046
  -9.500  -0.2700   0.10874   0.10429  -0.0435   1.0000   0.1068
  -9.250  -0.2675   0.10683   0.10245  -0.0403   1.0000   0.1088
  -9.000  -0.2790   0.10610   0.10183  -0.0367   1.0000   0.1102
  -8.750  -0.2979   0.10602   0.10189  -0.0326   1.0000   0.1114
  -8.500  -0.2913   0.10317   0.09908  -0.0364   0.9949   0.1163
  -8.250  -0.3065   0.09856   0.09456  -0.0563   0.9756   0.1208
  -8.000  -0.2459   0.09351   0.08941  -0.0495   0.9777   0.1269
  -7.750  -0.2500   0.08909   0.08502  -0.0671   0.9585   0.1360
  -7.500  -0.2100   0.08402   0.07992  -0.0651   0.9554   0.1399
  -7.250  -0.1810   0.07977   0.07564  -0.0711   0.9472   0.1483
  -7.000  -0.1655   0.07427   0.07013  -0.0804   0.9338   0.1556
  -6.750  -0.1561   0.06870   0.06443  -0.0936   0.9181   0.1689
  -6.500  -0.1126   0.06574   0.06149  -0.0915   0.9154   0.1746
  -6.250  -0.0990   0.06194   0.05762  -0.0963   0.9014   0.1880
  -6.000  -0.0860   0.05891   0.05452  -0.0990   0.8880   0.2027
  -5.750  -0.0707   0.05643   0.05198  -0.0998   0.8763   0.2186
  -5.500  -0.0859   0.03967   0.03342  -0.1116   0.8595   0.1069
  -5.250  -0.0591   0.03579   0.02914  -0.1122   0.8530   0.0971
  -5.000  -0.0447   0.03311   0.02582  -0.1105   0.8417   0.0932
  -4.750  -0.0172   0.03102   0.02331  -0.1105   0.8353   0.0937
  -4.500   0.0025   0.02944   0.02122  -0.1090   0.8253   0.0919
  -4.250   0.0320   0.02783   0.01925  -0.1088   0.8194   0.0917
  -4.000   0.0531   0.02682   0.01809  -0.1077   0.8099   0.0931
  -3.750   0.0847   0.02569   0.01681  -0.1079   0.8049   0.0968
  -3.500   0.1047   0.02512   0.01613  -0.1065   0.7952   0.0987
  -3.250   0.1358   0.02412   0.01496  -0.1064   0.7899   0.1009
  -3.000   0.1571   0.02371   0.01447  -0.1052   0.7812   0.1034
  -2.750   0.1848   0.02281   0.01359  -0.1047   0.7753   0.1075
  -2.500   0.2067   0.02241   0.01325  -0.1036   0.7680   0.1143
  -2.250   0.2308   0.02190   0.01276  -0.1027   0.7611   0.1260
  -2.000   0.2563   0.02118   0.01214  -0.1019   0.7557   0.1539
  -1.750   0.2671   0.01972   0.01225  -0.0994   0.7475   0.4737
  -1.500   0.2918   0.01928   0.01213  -0.0976   0.7426   0.6218
  -1.250   0.3076   0.01932   0.01246  -0.0949   0.7343   0.7128
  -1.000   0.3417   0.01883   0.01226  -0.0943   0.7288   0.8376
  -0.750   0.4565   0.01839   0.01166  -0.1100   0.7222   1.0000
  -0.500   0.4717   0.01858   0.01163  -0.1084   0.7148   1.0000
  -0.250   0.4938   0.01873   0.01155  -0.1075   0.7086   1.0000
   0.000   0.5124   0.01906   0.01173  -0.1061   0.7006   1.0000
   0.250   0.5416   0.01903   0.01146  -0.1060   0.6956   1.0000
   0.500   0.5571   0.01958   0.01193  -0.1042   0.6866   1.0000
   0.750   0.5862   0.01959   0.01174  -0.1041   0.6812   1.0000
   1.000   0.6037   0.02014   0.01223  -0.1025   0.6728   1.0000
   1.250   0.6317   0.02022   0.01215  -0.1023   0.6667   1.0000
   1.500   0.6515   0.02072   0.01258  -0.1010   0.6589   1.0000
   1.750   0.6780   0.02090   0.01264  -0.1006   0.6522   1.0000
   2.000   0.7005   0.02131   0.01299  -0.0997   0.6449   1.0000
   2.250   0.7246   0.02163   0.01322  -0.0990   0.6374   1.0000
   2.500   0.7509   0.02191   0.01341  -0.0986   0.6310   1.0000
   2.750   0.7712   0.02241   0.01389  -0.0974   0.6225   1.0000
   3.000   0.8039   0.02245   0.01378  -0.0978   0.6173   1.0000
   3.250   0.8176   0.02324   0.01464  -0.0958   0.6074   1.0000
   3.500   0.8499   0.02328   0.01454  -0.0961   0.6020   1.0000
   3.750   0.8635   0.02410   0.01544  -0.0942   0.5922   1.0000
   4.000   0.8952   0.02415   0.01538  -0.0944   0.5865   1.0000
   4.250   0.9088   0.02500   0.01632  -0.0925   0.5770   1.0000
   4.500   0.9399   0.02503   0.01627  -0.0927   0.5712   1.0000
   4.750   0.9539   0.02587   0.01720  -0.0908   0.5619   1.0000
   5.000   0.9838   0.02595   0.01721  -0.0908   0.5559   1.0000
   5.250   0.9987   0.02677   0.01812  -0.0891   0.5473   1.0000
   5.500   1.0271   0.02687   0.01819  -0.0889   0.5409   1.0000
   5.750   1.0442   0.02758   0.01898  -0.0875   0.5331   1.0000
   6.000   1.0688   0.02788   0.01928  -0.0869   0.5263   1.0000
   6.250   1.0931   0.02825   0.01967  -0.0863   0.5201   1.0000
   6.500   1.1094   0.02894   0.02044  -0.0847   0.5121   1.0000
   6.750   1.1465   0.02864   0.02009  -0.0857   0.5076   1.0000
   7.000   1.1485   0.03012   0.02176  -0.0825   0.4985   1.0000
   7.250   1.1825   0.02995   0.02156  -0.0831   0.4936   1.0000
   7.500   1.1883   0.03127   0.02306  -0.0804   0.4856   1.0000
   7.750   1.2164   0.03137   0.02319  -0.0803   0.4800   1.0000
   8.000   1.2380   0.03196   0.02384  -0.0794   0.4744   1.0000
   8.250   1.2462   0.03312   0.02514  -0.0771   0.4670   1.0000
   8.500   1.2925   0.03219   0.02415  -0.0790   0.4623   1.0000
   8.750   1.2827   0.03419   0.02639  -0.0745   0.4537   1.0000
   9.000   1.3277   0.03320   0.02536  -0.0761   0.4481   1.0000
   9.250   1.3234   0.03496   0.02730  -0.0723   0.4406   1.0000
   9.500   1.3538   0.03482   0.02723  -0.0724   0.4346   1.0000
   9.750   1.3718   0.03543   0.02794  -0.0711   0.4285   1.0000
  10.000   1.3752   0.03667   0.02933  -0.0682   0.4216   1.0000
  10.250   1.4340   0.03526   0.02785  -0.0715   0.4162   1.0000
  10.500   1.3984   0.03833   0.03121  -0.0643   0.4089   1.0000
  10.750   1.4661   0.03583   0.02864  -0.0681   0.4003   1.0000
  11.000   1.4382   0.03829   0.03134  -0.0615   0.3936   1.0000
  11.250   1.4805   0.03654   0.02956  -0.0622   0.3822   1.0000
  11.500   1.5137   0.03517   0.02812  -0.0619   0.3694   1.0000
  11.750   1.4974   0.03652   0.02965  -0.0563   0.3619   1.0000
  12.000   1.5121   0.03637   0.02952  -0.0542   0.3516   1.0000
  12.250   1.5304   0.03592   0.02901  -0.0525   0.3397   1.0000
  12.500   1.5091   0.03792   0.03124  -0.0477   0.3324   1.0000
  12.750   1.5158   0.03838   0.03173  -0.0454   0.3220   1.0000
  13.000   1.5143   0.03950   0.03294  -0.0428   0.3124   1.0000
  13.250   1.5017   0.04169   0.03530  -0.0400   0.3043   1.0000
  13.500   1.5054   0.04268   0.03635  -0.0382   0.2938   1.0000
  13.750   1.4857   0.04584   0.03971  -0.0360   0.2849   1.0000
  14.000   1.4735   0.04860   0.04259  -0.0345   0.2746   1.0000
  14.250   1.4623   0.05142   0.04549  -0.0333   0.2628   1.0000
  14.500   1.4466   0.05497   0.04911  -0.0325   0.2499   1.0000
  14.750   1.4272   0.05935   0.05357  -0.0323   0.2361   1.0000
  15.000   1.4048   0.06450   0.05881  -0.0326   0.2213   1.0000
  15.250   1.3807   0.07028   0.06465  -0.0333   0.2048   1.0000
  15.500   1.3568   0.07628   0.07063  -0.0343   0.1853   1.0000
  15.750   1.3347   0.08221   0.07639  -0.0354   0.1637   1.0000
  16.000   1.3123   0.08847   0.08248  -0.0368   0.1439   1.0000
  16.250   1.2911   0.09466   0.08840  -0.0382   0.1271   1.0000
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