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GOE 409 AIRFOIL (goe409-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 409 AIRFOIL (goe409-il)
Reynolds number: 50,000
Max Cl/Cd: 26.56 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe409-il-50000-n5.txt
Download as CSV file: xf-goe409-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 409 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7618   0.08653   0.07849  -0.0439   1.0000   0.0842
 -12.500  -0.7951   0.07932   0.07118  -0.0473   1.0000   0.0839
 -12.250  -0.8259   0.07359   0.06530  -0.0489   1.0000   0.0838
 -12.000  -0.8552   0.06895   0.06047  -0.0486   1.0000   0.0838
 -11.750  -0.8820   0.06518   0.05647  -0.0467   1.0000   0.0840
 -11.500  -0.8928   0.06216   0.05336  -0.0445   1.0000   0.0851
 -11.250  -0.8924   0.05987   0.05101  -0.0427   1.0000   0.0867
 -11.000  -0.8996   0.05741   0.04840  -0.0399   1.0000   0.0877
 -10.750  -0.9038   0.05485   0.04563  -0.0373   1.0000   0.0888
 -10.500  -0.9059   0.05232   0.04286  -0.0346   1.0000   0.0898
 -10.250  -0.9049   0.05006   0.04034  -0.0320   1.0000   0.0915
 -10.000  -0.9027   0.04781   0.03780  -0.0294   1.0000   0.0933
  -9.750  -0.8980   0.04562   0.03526  -0.0268   1.0000   0.0950
  -9.500  -0.8889   0.04350   0.03279  -0.0246   1.0000   0.0961
  -9.250  -0.8748   0.04154   0.03051  -0.0228   1.0000   0.0972
  -9.000  -0.8549   0.03984   0.02875  -0.0219   1.0000   0.0986
  -8.750  -0.8366   0.03843   0.02727  -0.0207   1.0000   0.1006
  -8.500  -0.8195   0.03718   0.02592  -0.0192   1.0000   0.1032
  -8.250  -0.8009   0.03593   0.02448  -0.0179   1.0000   0.1060
  -8.000  -0.7798   0.03470   0.02305  -0.0167   1.0000   0.1085
  -7.750  -0.7580   0.03356   0.02183  -0.0157   1.0000   0.1106
  -7.500  -0.7391   0.03256   0.02083  -0.0143   1.0000   0.1129
  -7.250  -0.7213   0.03165   0.01987  -0.0127   1.0000   0.1156
  -7.000  -0.7044   0.03079   0.01891  -0.0109   1.0000   0.1190
  -6.750  -0.6887   0.02999   0.01803  -0.0089   1.0000   0.1236
  -6.500  -0.6758   0.02919   0.01727  -0.0066   1.0000   0.1290
  -6.250  -0.6619   0.02845   0.01645  -0.0043   1.0000   0.1367
  -6.000  -0.6503   0.02762   0.01569  -0.0018   1.0000   0.1449
  -5.750  -0.6387   0.02678   0.01488   0.0008   1.0000   0.1571
  -5.500  -0.6277   0.02590   0.01409   0.0034   1.0000   0.1750
  -5.250  -0.6173   0.02498   0.01333   0.0060   1.0000   0.2033
  -5.000  -0.6075   0.02405   0.01265   0.0087   1.0000   0.2447
  -4.750  -0.5986   0.02313   0.01212   0.0116   1.0000   0.3012
  -4.500  -0.5905   0.02234   0.01184   0.0149   1.0000   0.3779
  -4.250  -0.5804   0.02185   0.01168   0.0181   1.0000   0.4582
  -4.000  -0.5670   0.02153   0.01148   0.0209   1.0000   0.5099
  -3.750  -0.5521   0.02129   0.01139   0.0235   1.0000   0.5550
  -3.500  -0.5360   0.02114   0.01134   0.0260   1.0000   0.5940
  -3.250  -0.5183   0.02106   0.01131   0.0282   1.0000   0.6271
  -3.000  -0.4999   0.02108   0.01144   0.0304   1.0000   0.6654
  -2.750  -0.4808   0.02122   0.01167   0.0327   1.0000   0.7065
  -2.500  -0.4583   0.02154   0.01208   0.0347   1.0000   0.7467
  -2.250  -0.4345   0.02201   0.01260   0.0365   1.0000   0.7869
  -2.000  -0.4053   0.02269   0.01327   0.0374   1.0000   0.8237
  -1.750  -0.3724   0.02339   0.01392   0.0374   1.0000   0.8546
  -1.500  -0.3171   0.02411   0.01451   0.0327   0.9945   0.8755
  -1.250  -0.2650   0.02447   0.01475   0.0276   0.9872   0.8902
  -1.000  -0.2123   0.02474   0.01490   0.0223   0.9798   0.9032
  -0.750  -0.1597   0.02497   0.01504   0.0168   0.9722   0.9158
  -0.500  -0.1054   0.02508   0.01509   0.0111   0.9638   0.9256
  -0.250  -0.0522   0.02516   0.01513   0.0054   0.9552   0.9357
   0.000   0.0000   0.02522   0.01517   0.0000   0.9463   0.9463
   0.250   0.0521   0.02516   0.01513  -0.0054   0.9358   0.9552
   0.500   0.1056   0.02508   0.01509  -0.0111   0.9256   0.9638
   0.750   0.1599   0.02497   0.01504  -0.0169   0.9158   0.9722
   1.000   0.2124   0.02474   0.01490  -0.0223   0.9032   0.9799
   1.250   0.2650   0.02447   0.01475  -0.0276   0.8902   0.9873
   1.500   0.3171   0.02411   0.01451  -0.0327   0.8756   0.9945
   1.750   0.3723   0.02338   0.01392  -0.0374   0.8546   1.0000
   2.000   0.4050   0.02270   0.01328  -0.0374   0.8240   1.0000
   2.250   0.4344   0.02200   0.01259  -0.0365   0.7869   1.0000
   2.500   0.4582   0.02154   0.01209  -0.0347   0.7471   1.0000
   2.750   0.4805   0.02121   0.01166  -0.0327   0.7052   1.0000
   3.000   0.4998   0.02107   0.01143  -0.0304   0.6650   1.0000
   3.250   0.5181   0.02105   0.01131  -0.0281   0.6264   1.0000
   3.500   0.5358   0.02114   0.01133  -0.0260   0.5937   1.0000
   3.750   0.5519   0.02129   0.01138  -0.0235   0.5543   1.0000
   4.000   0.5669   0.02153   0.01148  -0.0209   0.5101   1.0000
   4.250   0.5803   0.02185   0.01168  -0.0181   0.4584   1.0000
   4.500   0.5905   0.02234   0.01183  -0.0149   0.3783   1.0000
   4.750   0.5984   0.02313   0.01211  -0.0116   0.3008   1.0000
   5.000   0.6074   0.02404   0.01265  -0.0087   0.2452   1.0000
   5.250   0.6173   0.02497   0.01333  -0.0060   0.2036   1.0000
   5.500   0.6277   0.02589   0.01409  -0.0034   0.1751   1.0000
   5.750   0.6386   0.02678   0.01488  -0.0008   0.1571   1.0000
   6.000   0.6503   0.02761   0.01569   0.0018   0.1451   1.0000
   6.250   0.6619   0.02844   0.01644   0.0043   0.1368   1.0000
   6.500   0.6758   0.02919   0.01726   0.0066   0.1290   1.0000
   6.750   0.6886   0.02998   0.01802   0.0089   0.1236   1.0000
   7.000   0.7044   0.03079   0.01891   0.0109   0.1190   1.0000
   7.250   0.7214   0.03165   0.01987   0.0127   0.1156   1.0000
   7.500   0.7391   0.03256   0.02083   0.0143   0.1128   1.0000
   7.750   0.7580   0.03356   0.02182   0.0157   0.1105   1.0000
   8.000   0.7799   0.03469   0.02305   0.0167   0.1085   1.0000
   8.250   0.8009   0.03592   0.02449   0.0179   0.1060   1.0000
   8.500   0.8195   0.03717   0.02591   0.0192   0.1032   1.0000
   8.750   0.8368   0.03844   0.02728   0.0206   0.1007   1.0000
   9.000   0.8549   0.03984   0.02875   0.0219   0.0986   1.0000
   9.250   0.8749   0.04153   0.03050   0.0228   0.0972   1.0000
   9.500   0.8889   0.04350   0.03279   0.0245   0.0961   1.0000
   9.750   0.8982   0.04562   0.03526   0.0268   0.0950   1.0000
  10.000   0.9030   0.04783   0.03782   0.0293   0.0934   1.0000
  10.250   0.9052   0.05004   0.04032   0.0320   0.0914   1.0000
  10.500   0.9062   0.05232   0.04285   0.0346   0.0898   1.0000
  10.750   0.9043   0.05485   0.04563   0.0372   0.0887   1.0000
  11.000   0.9000   0.05743   0.04842   0.0398   0.0877   1.0000
  11.250   0.8931   0.05987   0.05101   0.0426   0.0866   1.0000
  11.500   0.8952   0.06215   0.05333   0.0443   0.0849   1.0000
  11.750   0.8823   0.06522   0.05651   0.0466   0.0840   1.0000
  12.000   0.8554   0.06900   0.06052   0.0485   0.0838   1.0000
  12.250   0.8260   0.07365   0.06536   0.0488   0.0837   1.0000
  12.500   0.7933   0.07955   0.07141   0.0471   0.0838   1.0000
  12.750   0.7609   0.08678   0.07875   0.0436   0.0841   1.0000
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