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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 200,000
Max Cl/Cd: 77.55 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe596-il-200000.txt
Download as CSV file: xf-goe596-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3569   0.08977   0.08632  -0.0377   1.0000   0.0515
  -8.000  -0.3756   0.08793   0.08458  -0.0380   1.0000   0.0517
  -7.750  -0.3904   0.08560   0.08230  -0.0390   1.0000   0.0519
  -7.500  -0.4044   0.08316   0.07986  -0.0393   1.0000   0.0520
  -7.250  -0.4113   0.07911   0.07589  -0.0361   1.0000   0.0526
  -7.000  -0.4124   0.07709   0.07394  -0.0316   1.0000   0.0532
  -6.750  -0.3980   0.07476   0.07162  -0.0306   0.9980   0.0544
  -6.500  -0.3697   0.07072   0.06754  -0.0361   0.9932   0.0566
  -6.250  -0.3201   0.06290   0.05916  -0.0570   0.9834   0.0631
  -6.000  -0.3022   0.05657   0.05286  -0.0599   0.9769   0.0644
  -5.750  -0.2747   0.05375   0.05012  -0.0616   0.9728   0.0660
  -5.500  -0.2457   0.05103   0.04735  -0.0645   0.9670   0.0693
  -5.250  -0.2085   0.04512   0.04087  -0.0725   0.9592   0.0776
  -5.000  -0.1758   0.04227   0.03810  -0.0753   0.9555   0.0798
  -4.750  -0.1464   0.03991   0.03564  -0.0772   0.9472   0.0843
  -4.500  -0.1069   0.03599   0.03131  -0.0820   0.9430   0.0934
  -4.250  -0.0733   0.03522   0.03027  -0.0835   0.9347   0.1044
  -4.000  -0.0426   0.03149   0.02656  -0.0860   0.9289   0.1101
  -3.750  -0.0126   0.02964   0.02441  -0.0872   0.9196   0.1236
  -3.500   0.0205   0.02801   0.02261  -0.0887   0.9119   0.1386
  -3.250   0.0467   0.02665   0.02115  -0.0887   0.9000   0.1539
  -3.000   0.0860   0.02106   0.01414  -0.0871   0.8907   0.0773
  -2.750   0.1166   0.01931   0.01225  -0.0872   0.8798   0.0736
  -2.500   0.1438   0.01770   0.01039  -0.0864   0.8657   0.0701
  -2.250   0.1716   0.01653   0.00896  -0.0856   0.8510   0.0679
  -2.000   0.1989   0.01566   0.00790  -0.0849   0.8357   0.0674
  -1.750   0.2258   0.01495   0.00706  -0.0841   0.8196   0.0677
  -1.500   0.2520   0.01442   0.00646  -0.0833   0.8026   0.0700
  -1.250   0.2780   0.01394   0.00589  -0.0824   0.7855   0.0721
  -1.000   0.3037   0.01348   0.00534  -0.0816   0.7690   0.0735
  -0.750   0.3292   0.01312   0.00490  -0.0807   0.7535   0.0753
  -0.500   0.3539   0.01267   0.00443  -0.0799   0.7388   0.0784
  -0.250   0.3791   0.01240   0.00414  -0.0791   0.7249   0.0843
   0.000   0.4046   0.01218   0.00389  -0.0784   0.7119   0.0951
   0.250   0.4282   0.01155   0.00367  -0.0776   0.7004   0.2178
   0.500   0.5030   0.00959   0.00357  -0.0870   0.6884   1.0000
   0.750   0.5274   0.00973   0.00355  -0.0861   0.6773   1.0000
   1.000   0.5517   0.00989   0.00359  -0.0853   0.6666   1.0000
   1.250   0.5764   0.01006   0.00362  -0.0845   0.6572   1.0000
   1.500   0.6009   0.01023   0.00369  -0.0837   0.6472   1.0000
   1.750   0.6254   0.01042   0.00379  -0.0830   0.6375   1.0000
   2.000   0.6506   0.01063   0.00388  -0.0823   0.6289   1.0000
   2.250   0.6748   0.01081   0.00404  -0.0815   0.6194   1.0000
   2.500   0.7000   0.01104   0.00417  -0.0808   0.6110   1.0000
   2.750   0.7244   0.01123   0.00434  -0.0801   0.6012   1.0000
   3.000   0.7490   0.01144   0.00451  -0.0793   0.5920   1.0000
   3.250   0.7739   0.01165   0.00465  -0.0786   0.5825   1.0000
   3.500   0.7978   0.01184   0.00485  -0.0777   0.5715   1.0000
   3.750   0.8222   0.01204   0.00501  -0.0770   0.5611   1.0000
   4.000   0.8468   0.01223   0.00515  -0.0762   0.5506   1.0000
   4.250   0.8705   0.01240   0.00536  -0.0753   0.5390   1.0000
   4.500   0.8945   0.01259   0.00553  -0.0744   0.5278   1.0000
   4.750   0.9186   0.01277   0.00567  -0.0736   0.5163   1.0000
   5.000   0.9420   0.01292   0.00580  -0.0726   0.5030   1.0000
   5.250   0.9646   0.01304   0.00595  -0.0715   0.4884   1.0000
   5.500   0.9874   0.01318   0.00611  -0.0704   0.4739   1.0000
   5.750   1.0100   0.01333   0.00627  -0.0693   0.4587   1.0000
   6.000   1.0324   0.01349   0.00645  -0.0682   0.4429   1.0000
   6.250   1.0549   0.01369   0.00667  -0.0672   0.4276   1.0000
   6.500   1.0768   0.01392   0.00689  -0.0660   0.4113   1.0000
   6.750   1.0981   0.01416   0.00714  -0.0648   0.3927   1.0000
   7.000   1.1188   0.01446   0.00745  -0.0635   0.3726   1.0000
   7.250   1.1377   0.01485   0.00777  -0.0619   0.3492   1.0000
   7.500   1.1561   0.01530   0.00817  -0.0603   0.3226   1.0000
   7.750   1.1718   0.01588   0.00863  -0.0583   0.2851   1.0000
   8.000   1.1811   0.01688   0.00929  -0.0555   0.2140   1.0000
   8.250   1.1792   0.01881   0.01056  -0.0513   0.1219   1.0000
   8.500   1.1816   0.02043   0.01181  -0.0477   0.0829   1.0000
   8.750   1.1894   0.02150   0.01287  -0.0447   0.0741   1.0000
   9.000   1.1933   0.02264   0.01402  -0.0411   0.0691   1.0000
   9.250   1.2005   0.02364   0.01511  -0.0382   0.0656   1.0000
   9.500   1.2047   0.02485   0.01639  -0.0351   0.0625   1.0000
   9.750   1.2041   0.02646   0.01799  -0.0318   0.0599   1.0000
  10.000   1.2088   0.02786   0.01947  -0.0292   0.0579   1.0000
  10.250   1.2160   0.02919   0.02089  -0.0271   0.0558   1.0000
  10.500   1.2226   0.03065   0.02241  -0.0252   0.0538   1.0000
  10.750   1.2290   0.03225   0.02403  -0.0233   0.0518   1.0000
  11.000   1.2370   0.03425   0.02598  -0.0216   0.0495   1.0000
  11.250   1.2494   0.03574   0.02757  -0.0202   0.0479   1.0000
  11.500   1.2631   0.03716   0.02909  -0.0190   0.0464   1.0000
  11.750   1.2768   0.03867   0.03069  -0.0178   0.0446   1.0000
  12.000   1.2889   0.04024   0.03230  -0.0167   0.0428   1.0000
  12.250   1.3260   0.04288   0.03485  -0.0173   0.0401   1.0000
  12.500   1.3320   0.04454   0.03674  -0.0157   0.0395   1.0000
  12.750   1.3390   0.04647   0.03889  -0.0142   0.0386   1.0000
  13.000   1.3455   0.04859   0.04122  -0.0130   0.0377   1.0000
  13.250   1.3505   0.05083   0.04365  -0.0118   0.0366   1.0000
  13.500   1.3558   0.05302   0.04598  -0.0108   0.0355   1.0000
  13.750   1.3625   0.05526   0.04831  -0.0100   0.0345   1.0000
  14.000   1.3693   0.05805   0.05122  -0.0094   0.0338   1.0000
  14.250   1.3804   0.06231   0.05563  -0.0090   0.0330   1.0000
  14.750   1.3603   0.07102   0.06484  -0.0078   0.0327   1.0000
  15.000   1.3436   0.07498   0.06905  -0.0078   0.0326   1.0000
  15.250   1.3272   0.07952   0.07382  -0.0083   0.0326   1.0000
  15.500   1.3074   0.08435   0.07888  -0.0095   0.0325   1.0000
  15.750   1.2902   0.08986   0.08460  -0.0111   0.0326   1.0000
  16.000   1.2700   0.09575   0.09070  -0.0134   0.0326   1.0000
  16.250   1.2484   0.10197   0.09713  -0.0163   0.0326   1.0000
  16.500   1.2301   0.10897   0.10430  -0.0193   0.0327   1.0000
  17.000   1.0727   0.14979   0.14606  -0.0495   0.0378   1.0000
  17.250   1.0423   0.16398   0.16029  -0.0577   0.0395   1.0000
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