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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 200,000
Max Cl/Cd: 66.05 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe585-il-200000-n5.txt
Download as CSV file: xf-goe585-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4075   0.08798   0.08434  -0.0288   1.0000   0.0223
  -8.500  -0.4132   0.08421   0.08063  -0.0299   1.0000   0.0230
  -8.250  -0.4225   0.08058   0.07707  -0.0305   1.0000   0.0235
  -8.000  -0.4346   0.07736   0.07395  -0.0304   1.0000   0.0236
  -7.750  -0.4440   0.07284   0.06948  -0.0324   1.0000   0.0238
  -7.500  -0.4522   0.06796   0.06463  -0.0346   1.0000   0.0240
  -7.250  -0.4591   0.06250   0.05915  -0.0369   1.0000   0.0242
  -7.000  -0.4601   0.04607   0.04236  -0.0491   0.9963   0.0250
  -6.750  -0.4333   0.04412   0.04030  -0.0523   0.9923   0.0260
  -6.500  -0.4046   0.04308   0.03918  -0.0545   0.9884   0.0273
  -6.250  -0.3814   0.03424   0.02971  -0.0599   0.9826   0.0290
  -6.000  -0.3568   0.02806   0.02273  -0.0626   0.9772   0.0310
  -5.750  -0.3287   0.02521   0.01925  -0.0638   0.9727   0.0326
  -5.500  -0.3017   0.02260   0.01613  -0.0645   0.9677   0.0336
  -5.250  -0.2707   0.02088   0.01419  -0.0659   0.9645   0.0351
  -5.000  -0.2422   0.01994   0.01312  -0.0663   0.9593   0.0366
  -4.750  -0.2116   0.01880   0.01173  -0.0670   0.9548   0.0377
  -4.500  -0.1781   0.01772   0.01042  -0.0682   0.9516   0.0386
  -4.250  -0.1480   0.01681   0.00934  -0.0686   0.9468   0.0395
  -4.000  -0.1171   0.01610   0.00848  -0.0692   0.9416   0.0411
  -3.750  -0.0829   0.01541   0.00767  -0.0704   0.9381   0.0423
  -3.500  -0.0497   0.01474   0.00690  -0.0714   0.9341   0.0429
  -3.250  -0.0210   0.01413   0.00623  -0.0715   0.9273   0.0437
  -3.000   0.0123   0.01348   0.00558  -0.0725   0.9227   0.0452
  -2.750   0.0436   0.01302   0.00509  -0.0730   0.9145   0.0470
  -2.500   0.0800   0.01256   0.00458  -0.0745   0.9057   0.0491
  -2.250   0.1111   0.01221   0.00418  -0.0748   0.8925   0.0524
  -2.000   0.1415   0.01188   0.00384  -0.0750   0.8794   0.0572
  -1.750   0.1712   0.01158   0.00354  -0.0751   0.8657   0.0660
  -1.500   0.1998   0.01129   0.00332  -0.0750   0.8522   0.0883
  -1.250   0.2280   0.01107   0.00315  -0.0748   0.8390   0.1159
  -1.000   0.2558   0.01088   0.00299  -0.0746   0.8248   0.1420
  -0.750   0.2830   0.01067   0.00286  -0.0743   0.8092   0.1742
  -0.500   0.3096   0.01042   0.00276  -0.0738   0.7926   0.2321
  -0.250   0.3352   0.01010   0.00271  -0.0733   0.7752   0.3336
   0.000   0.3557   0.00934   0.00266  -0.0718   0.7578   0.5540
   0.250   0.4367   0.00848   0.00261  -0.0822   0.7351   1.0000
   0.500   0.4611   0.00860   0.00256  -0.0812   0.7142   1.0000
   0.750   0.4850   0.00873   0.00253  -0.0801   0.6927   1.0000
   1.000   0.5086   0.00887   0.00252  -0.0789   0.6694   1.0000
   1.250   0.5319   0.00903   0.00253  -0.0778   0.6450   1.0000
   1.500   0.5549   0.00920   0.00256  -0.0765   0.6172   1.0000
   1.750   0.5774   0.00940   0.00259  -0.0752   0.5853   1.0000
   2.000   0.5992   0.00965   0.00264  -0.0738   0.5465   1.0000
   2.250   0.6200   0.00996   0.00272  -0.0722   0.5024   1.0000
   2.500   0.6407   0.01032   0.00284  -0.0707   0.4615   1.0000
   2.750   0.6621   0.01066   0.00299  -0.0694   0.4309   1.0000
   3.000   0.6842   0.01099   0.00317  -0.0682   0.4069   1.0000
   3.250   0.7070   0.01130   0.00338  -0.0671   0.3859   1.0000
   3.500   0.7298   0.01160   0.00358  -0.0661   0.3671   1.0000
   3.750   0.7529   0.01190   0.00380  -0.0651   0.3509   1.0000
   4.000   0.7764   0.01218   0.00404  -0.0642   0.3369   1.0000
   4.250   0.7999   0.01247   0.00428  -0.0634   0.3245   1.0000
   4.500   0.8234   0.01276   0.00454  -0.0625   0.3130   1.0000
   5.000   0.8704   0.01335   0.00510  -0.0608   0.2906   1.0000
   5.250   0.8940   0.01366   0.00540  -0.0600   0.2810   1.0000
   5.500   0.9172   0.01399   0.00572  -0.0591   0.2721   1.0000
   5.750   0.9408   0.01429   0.00605  -0.0583   0.2616   1.0000
   6.000   0.9638   0.01461   0.00637  -0.0574   0.2496   1.0000
   6.250   0.9866   0.01495   0.00670  -0.0566   0.2369   1.0000
   6.500   1.0091   0.01531   0.00706  -0.0556   0.2262   1.0000
   6.750   1.0324   0.01563   0.00744  -0.0548   0.2175   1.0000
   7.000   1.0550   0.01600   0.00784  -0.0539   0.2094   1.0000
   7.250   1.0775   0.01637   0.00825  -0.0530   0.2002   1.0000
   7.500   1.1000   0.01673   0.00869  -0.0521   0.1901   1.0000
   7.750   1.1218   0.01713   0.00913  -0.0511   0.1785   1.0000
   8.000   1.1428   0.01757   0.00956  -0.0501   0.1616   1.0000
   8.250   1.1628   0.01811   0.01004  -0.0489   0.1416   1.0000
   8.500   1.1824   0.01870   0.01059  -0.0478   0.1174   1.0000
   8.750   1.1993   0.01954   0.01130  -0.0463   0.0912   1.0000
   9.000   1.2154   0.02045   0.01213  -0.0447   0.0731   1.0000
   9.250   1.2315   0.02135   0.01301  -0.0430   0.0602   1.0000
   9.500   1.2468   0.02226   0.01393  -0.0413   0.0490   1.0000
   9.750   1.2611   0.02323   0.01491  -0.0395   0.0382   1.0000
  10.000   1.2737   0.02427   0.01596  -0.0374   0.0299   1.0000
  10.250   1.2840   0.02534   0.01709  -0.0350   0.0254   1.0000
  10.500   1.2929   0.02638   0.01823  -0.0323   0.0223   1.0000
  10.750   1.2992   0.02759   0.01950  -0.0295   0.0204   1.0000
  11.000   1.3058   0.02877   0.02081  -0.0269   0.0188   1.0000
  11.250   1.3114   0.03004   0.02221  -0.0244   0.0176   1.0000
  11.500   1.3153   0.03146   0.02376  -0.0219   0.0169   1.0000
  11.750   1.3170   0.03311   0.02554  -0.0195   0.0162   1.0000
  12.000   1.3152   0.03512   0.02766  -0.0172   0.0155   1.0000
  12.250   1.3105   0.03748   0.03016  -0.0152   0.0150   1.0000
  12.500   1.3075   0.03992   0.03272  -0.0137   0.0146   1.0000
  12.750   1.3065   0.04233   0.03533  -0.0127   0.0143   1.0000
  13.000   1.3043   0.04504   0.03821  -0.0120   0.0138   1.0000
  13.250   1.3004   0.04813   0.04145  -0.0118   0.0135   1.0000
  13.500   1.2962   0.05144   0.04491  -0.0119   0.0131   1.0000
  13.750   1.2915   0.05501   0.04863  -0.0125   0.0126   1.0000
  14.000   1.2840   0.05915   0.05292  -0.0133   0.0125   1.0000
  14.250   1.2770   0.06344   0.05735  -0.0147   0.0123   1.0000
  14.500   1.2685   0.06817   0.06223  -0.0164   0.0120   1.0000
  14.750   1.2598   0.07315   0.06735  -0.0184   0.0119   1.0000
  15.000   1.2511   0.07829   0.07263  -0.0205   0.0118   1.0000
  15.250   1.2411   0.08384   0.07830  -0.0230   0.0116   1.0000
  15.500   1.2328   0.08920   0.08380  -0.0254   0.0115   1.0000
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