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GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 178 AIRFOIL (goe178-il)
Reynolds number: 200,000
Max Cl/Cd: 78.11 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe178-il-200000.txt
Download as CSV file: xf-goe178-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 178 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3557   0.09205   0.08873  -0.0179   1.0000   0.0445
  -7.500  -0.3507   0.08921   0.08593  -0.0193   1.0000   0.0467
  -7.250  -0.3493   0.08642   0.08320  -0.0250   1.0000   0.0496
  -7.000  -0.3384   0.08246   0.07924  -0.0398   1.0000   0.0506
  -6.750  -0.3387   0.07800   0.07486  -0.0342   1.0000   0.0516
  -6.500  -0.3323   0.07567   0.07257  -0.0310   1.0000   0.0528
  -6.250  -0.3260   0.07328   0.07020  -0.0304   1.0000   0.0544
  -6.000  -0.3199   0.07064   0.06759  -0.0314   1.0000   0.0566
  -5.750  -0.2938   0.06614   0.06284  -0.0471   1.0000   0.0618
  -5.500  -0.2928   0.06122   0.05799  -0.0463   1.0000   0.0626
  -5.250  -0.2766   0.05864   0.05549  -0.0447   0.9970   0.0643
  -5.000  -0.2403   0.05530   0.05210  -0.0494   0.9919   0.0691
  -4.750  -0.1794   0.04723   0.04359  -0.0653   0.9854   0.0762
  -4.500  -0.1456   0.04415   0.04052  -0.0684   0.9797   0.0786
  -4.250  -0.0883   0.03919   0.03489  -0.0786   0.9734   0.0895
  -4.000  -0.0534   0.03549   0.03130  -0.0819   0.9675   0.0917
  -3.750  -0.0149   0.03272   0.02841  -0.0854   0.9586   0.0955
  -3.500   0.0340   0.02537   0.01991  -0.0905   0.9481   0.0763
  -3.250   0.0724   0.02094   0.01465  -0.0919   0.9350   0.0622
  -3.000   0.1035   0.01865   0.01208  -0.0924   0.9166   0.0611
  -2.750   0.1326   0.01701   0.01012  -0.0921   0.8937   0.0610
  -2.500   0.1604   0.01581   0.00863  -0.0913   0.8673   0.0613
  -2.250   0.1865   0.01474   0.00729  -0.0903   0.8365   0.0628
  -2.000   0.2116   0.01412   0.00651  -0.0891   0.8018   0.0655
  -1.750   0.2370   0.01365   0.00581  -0.0880   0.7644   0.0673
  -1.500   0.2629   0.01326   0.00520  -0.0871   0.7240   0.0699
  -1.250   0.2893   0.01300   0.00467  -0.0864   0.6867   0.0738
  -1.000   0.3160   0.01264   0.00419  -0.0860   0.6567   0.0808
  -0.750   0.3433   0.01237   0.00379  -0.0857   0.6339   0.0991
  -0.500   0.3710   0.01218   0.00355  -0.0857   0.6156   0.1332
  -0.250   0.3986   0.01214   0.00349  -0.0857   0.6006   0.1602
   0.250   0.4539   0.01159   0.00352  -0.0860   0.5770   0.3793
   0.500   0.4752   0.01024   0.00351  -0.0840   0.5681   1.0000
   0.750   0.5032   0.01048   0.00351  -0.0839   0.5589   1.0000
   1.000   0.5313   0.01065   0.00355  -0.0839   0.5489   1.0000
   1.250   0.5592   0.01087   0.00361  -0.0838   0.5401   1.0000
   1.500   0.5871   0.01107   0.00368  -0.0837   0.5314   1.0000
   1.750   0.6151   0.01128   0.00379  -0.0837   0.5239   1.0000
   2.000   0.6431   0.01149   0.00392  -0.0837   0.5173   1.0000
   2.250   0.6711   0.01173   0.00407  -0.0837   0.5113   1.0000
   2.500   0.6990   0.01193   0.00424  -0.0837   0.5048   1.0000
   2.750   0.7269   0.01220   0.00441  -0.0836   0.4996   1.0000
   3.000   0.7548   0.01240   0.00464  -0.0837   0.4935   1.0000
   3.250   0.7824   0.01263   0.00481  -0.0836   0.4866   1.0000
   3.500   0.8099   0.01284   0.00502  -0.0835   0.4791   1.0000
   3.750   0.8373   0.01305   0.00519  -0.0834   0.4713   1.0000
   4.000   0.8646   0.01327   0.00543  -0.0833   0.4639   1.0000
   4.250   0.8920   0.01349   0.00565  -0.0832   0.4572   1.0000
   4.500   0.9193   0.01374   0.00593  -0.0831   0.4506   1.0000
   4.750   0.9464   0.01394   0.00616  -0.0830   0.4429   1.0000
   5.000   0.9733   0.01417   0.00643  -0.0828   0.4350   1.0000
   5.250   1.0003   0.01438   0.00667  -0.0826   0.4275   1.0000
   5.500   1.0269   0.01458   0.00694  -0.0824   0.4186   1.0000
   5.750   1.0531   0.01471   0.00710  -0.0821   0.4075   1.0000
   6.000   1.0788   0.01477   0.00719  -0.0817   0.3940   1.0000
   6.250   1.1044   0.01480   0.00729  -0.0813   0.3786   1.0000
   6.500   1.1302   0.01490   0.00749  -0.0809   0.3647   1.0000
   6.750   1.1560   0.01499   0.00770  -0.0806   0.3477   1.0000
   7.000   1.1810   0.01512   0.00785  -0.0801   0.3222   1.0000
   7.250   1.2043   0.01548   0.00810  -0.0795   0.2804   1.0000
   7.500   1.2210   0.01678   0.00894  -0.0782   0.2009   1.0000
   7.750   1.2214   0.02049   0.01168  -0.0753   0.0521   1.0000
   8.000   1.2374   0.02197   0.01328  -0.0738   0.0407   1.0000
   8.250   1.2531   0.02329   0.01470  -0.0723   0.0359   1.0000
   8.500   1.2659   0.02477   0.01632  -0.0704   0.0335   1.0000
   8.750   1.2789   0.02612   0.01778  -0.0685   0.0317   1.0000
   9.000   1.2904   0.02750   0.01925  -0.0665   0.0300   1.0000
   9.250   1.3004   0.02890   0.02072  -0.0645   0.0284   1.0000
   9.500   1.3012   0.03087   0.02272  -0.0614   0.0270   1.0000
   9.750   1.3042   0.03275   0.02467  -0.0585   0.0263   1.0000
  10.000   1.3110   0.03450   0.02652  -0.0562   0.0259   1.0000
  10.250   1.3195   0.03637   0.02847  -0.0542   0.0254   1.0000
  10.500   1.3305   0.03831   0.03050  -0.0523   0.0250   1.0000
  10.750   1.3452   0.04038   0.03268  -0.0506   0.0247   1.0000
  11.000   1.3637   0.04270   0.03516  -0.0493   0.0245   1.0000
  11.250   1.3820   0.04530   0.03793  -0.0481   0.0244   1.0000
  11.500   1.3931   0.04777   0.04061  -0.0465   0.0239   1.0000
  11.750   1.4003   0.05031   0.04336  -0.0449   0.0234   1.0000
  12.000   1.4053   0.05331   0.04661  -0.0432   0.0232   1.0000
  12.250   1.4075   0.05724   0.05085  -0.0414   0.0238   1.0000
  12.500   1.4040   0.06133   0.05523  -0.0398   0.0244   1.0000
  12.750   1.3965   0.06562   0.05977  -0.0385   0.0249   1.0000
  13.000   1.3868   0.07023   0.06461  -0.0376   0.0255   1.0000
  13.250   1.4031   0.07472   0.06922  -0.0367   0.0274   1.0000
  13.500   1.3470   0.08126   0.07643  -0.0378   0.0296   1.0000
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