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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.11 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe240-il-1000000.txt
Download as CSV file: xf-goe240-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3183   0.09666   0.09509  -0.0258   1.0000   0.0119
  -8.250  -0.3165   0.09441   0.09286  -0.0257   1.0000   0.0122
  -8.000  -0.3108   0.09165   0.09013  -0.0268   0.9988   0.0126
  -7.750  -0.2928   0.08728   0.08576  -0.0325   0.9953   0.0138
  -7.500  -0.2718   0.08180   0.08027  -0.0427   0.9882   0.0142
  -7.250  -0.2477   0.07669   0.07514  -0.0508   0.9829   0.0142
  -7.000  -0.2287   0.07220   0.07064  -0.0564   0.9733   0.0142
  -6.750  -0.2179   0.06779   0.06621  -0.0589   0.9630   0.0146
  -6.500  -0.2028   0.06540   0.06380  -0.0604   0.9506   0.0148
  -6.250  -0.1860   0.06282   0.06117  -0.0626   0.9335   0.0151
  -6.000  -0.1677   0.06008   0.05834  -0.0651   0.8998   0.0158
  -5.750  -0.1331   0.05482   0.05278  -0.0738   0.8530   0.0180
  -5.500  -0.1054   0.05017   0.04794  -0.0789   0.8329   0.0181
  -5.250  -0.0764   0.04537   0.04296  -0.0836   0.8214   0.0182
  -4.750  -0.0303   0.03902   0.03640  -0.0885   0.8057   0.0193
  -4.500  -0.0040   0.03718   0.03446  -0.0901   0.7990   0.0207
  -4.250   0.0361   0.03265   0.02967  -0.0937   0.7932   0.0230
  -4.000   0.0668   0.02790   0.02464  -0.0958   0.7872   0.0231
  -2.250   0.2586   0.01350   0.00872  -0.0996   0.7457   0.0334
  -2.000   0.2867   0.01281   0.00788  -0.0996   0.7395   0.0354
  -1.750   0.3150   0.01179   0.00662  -0.0996   0.7342   0.0400
  -1.500   0.3429   0.01129   0.00608  -0.0997   0.7277   0.0417
  -1.250   0.3722   0.00935   0.00373  -0.0991   0.7210   0.0310
  -1.000   0.4003   0.00887   0.00318  -0.0990   0.7119   0.0309
  -0.750   0.4282   0.00847   0.00272  -0.0989   0.7028   0.0311
  -0.500   0.4560   0.00817   0.00236  -0.0988   0.6926   0.0315
  -0.250   0.4840   0.00792   0.00208  -0.0987   0.6812   0.0317
   0.000   0.5118   0.00775   0.00185  -0.0986   0.6660   0.0319
   0.250   0.5394   0.00763   0.00166  -0.0985   0.6468   0.0321
   0.500   0.5668   0.00757   0.00150  -0.0983   0.6209   0.0328
   0.750   0.5932   0.00766   0.00140  -0.0980   0.5775   0.0333
   1.000   0.6198   0.00778   0.00135  -0.0977   0.5455   0.0339
   1.250   0.6470   0.00783   0.00132  -0.0976   0.5252   0.0350
   1.500   0.6744   0.00790   0.00131  -0.0974   0.5084   0.0365
   1.750   0.7018   0.00797   0.00132  -0.0973   0.4932   0.0378
   2.000   0.7292   0.00806   0.00135  -0.0972   0.4766   0.0406
   2.250   0.7565   0.00811   0.00143  -0.0971   0.4600   0.0705
   2.500   0.7837   0.00820   0.00152  -0.0970   0.4412   0.0944
   2.750   0.8106   0.00813   0.00166  -0.0970   0.4163   0.2421
   3.000   0.8332   0.00688   0.00191  -0.0964   0.3877   1.0000
   3.250   0.8592   0.00719   0.00205  -0.0961   0.3564   1.0000
   3.500   0.8852   0.00749   0.00220  -0.0959   0.3303   1.0000
   3.750   0.9111   0.00779   0.00237  -0.0956   0.3059   1.0000
   4.000   0.9374   0.00803   0.00252  -0.0954   0.2878   1.0000
   4.250   0.9636   0.00829   0.00269  -0.0952   0.2689   1.0000
   4.500   0.9893   0.00859   0.00287  -0.0949   0.2442   1.0000
   4.750   1.0126   0.00920   0.00318  -0.0943   0.1911   1.0000
   5.000   1.0369   0.00967   0.00347  -0.0938   0.1616   1.0000
   5.250   1.0622   0.00999   0.00373  -0.0935   0.1467   1.0000
   5.500   1.0875   0.01031   0.00397  -0.0931   0.1337   1.0000
   5.750   1.1128   0.01061   0.00421  -0.0928   0.1226   1.0000
   6.000   1.1379   0.01093   0.00447  -0.0924   0.1113   1.0000
   6.250   1.1620   0.01136   0.00477  -0.0919   0.0890   1.0000
   6.500   1.1835   0.01209   0.00530  -0.0911   0.0557   1.0000
   6.750   1.2084   0.01240   0.00562  -0.0907   0.0509   1.0000
   7.000   1.2322   0.01282   0.00604  -0.0901   0.0440   1.0000
   7.250   1.2560   0.01323   0.00640  -0.0895   0.0324   1.0000
   7.500   1.2767   0.01400   0.00704  -0.0885   0.0152   1.0000
   7.750   1.3002   0.01442   0.00751  -0.0878   0.0137   1.0000
   8.000   1.3230   0.01489   0.00804  -0.0871   0.0127   1.0000
   8.250   1.3447   0.01547   0.00869  -0.0861   0.0117   1.0000
   8.500   1.3639   0.01632   0.00963  -0.0848   0.0106   1.0000
   8.750   1.3851   0.01688   0.01025  -0.0839   0.0103   1.0000
   9.000   1.4060   0.01745   0.01087  -0.0829   0.0099   1.0000
   9.250   1.4261   0.01805   0.01154  -0.0818   0.0094   1.0000
   9.500   1.4454   0.01870   0.01224  -0.0806   0.0089   1.0000
   9.750   1.4630   0.01945   0.01305  -0.0792   0.0084   1.0000
  10.000   1.4778   0.02040   0.01407  -0.0773   0.0080   1.0000
  10.250   1.4838   0.02194   0.01573  -0.0742   0.0076   1.0000
  10.500   1.4866   0.02333   0.01723  -0.0705   0.0074   1.0000
  10.750   1.4986   0.02411   0.01810  -0.0684   0.0073   1.0000
  11.000   1.5083   0.02508   0.01914  -0.0660   0.0072   1.0000
  11.250   1.5158   0.02623   0.02038  -0.0636   0.0070   1.0000
  11.500   1.5220   0.02753   0.02177  -0.0612   0.0068   1.0000
  11.750   1.5273   0.02898   0.02331  -0.0589   0.0067   1.0000
  12.000   1.5315   0.03060   0.02503  -0.0568   0.0065   1.0000
  12.250   1.5350   0.03240   0.02692  -0.0550   0.0064   1.0000
  12.500   1.5380   0.03437   0.02899  -0.0535   0.0062   1.0000
  12.750   1.5412   0.03643   0.03114  -0.0522   0.0061   1.0000
  13.000   1.5443   0.03859   0.03339  -0.0512   0.0059   1.0000
  13.250   1.5464   0.04092   0.03580  -0.0504   0.0058   1.0000
  13.500   1.5466   0.04354   0.03851  -0.0497   0.0056   1.0000
  13.750   1.5437   0.04658   0.04163  -0.0491   0.0055   1.0000
  14.000   1.5364   0.05019   0.04534  -0.0485   0.0054   1.0000
  14.250   1.5254   0.05434   0.04961  -0.0480   0.0053   1.0000
  14.500   1.5099   0.05907   0.05447  -0.0473   0.0052   1.0000
  14.750   1.4976   0.06363   0.05916  -0.0469   0.0051   1.0000
  15.000   1.4936   0.06751   0.06317  -0.0476   0.0051   1.0000
  15.250   1.4887   0.07165   0.06744  -0.0486   0.0050   1.0000
  15.500   1.4826   0.07610   0.07202  -0.0498   0.0050   1.0000
  15.750   1.4753   0.08085   0.07691  -0.0511   0.0050   1.0000
  16.000   1.4673   0.08580   0.08197  -0.0527   0.0049   1.0000
  16.250   1.4580   0.09105   0.08736  -0.0544   0.0049   1.0000
  16.500   1.4482   0.09651   0.09294  -0.0564   0.0049   1.0000
  16.750   1.4376   0.10222   0.09878  -0.0585   0.0049   1.0000
  17.000   1.4266   0.10812   0.10481  -0.0609   0.0048   1.0000
  17.250   1.4149   0.11424   0.11106  -0.0636   0.0048   1.0000
  17.500   1.4034   0.12055   0.11750  -0.0665   0.0048   1.0000
  17.750   1.3917   0.12704   0.12411  -0.0697   0.0048   1.0000
  18.000   1.3794   0.13377   0.13097  -0.0731   0.0048   1.0000
  18.250   1.3673   0.14064   0.13796  -0.0768   0.0048   1.0000
  18.500   1.3551   0.14771   0.14516  -0.0807   0.0048   1.0000
  18.750   1.3433   0.15494   0.15251  -0.0850   0.0048   1.0000
  19.000   1.3310   0.16254   0.16024  -0.0896   0.0048   1.0000
  19.250   1.3186   0.17041   0.16822  -0.0945   0.0048   1.0000
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