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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 50,000
Max Cl/Cd: 37.42 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe585-il-50000-n5.txt
Download as CSV file: xf-goe585-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3906   0.10266   0.09557  -0.0250   1.0000   0.1216
  -8.250  -0.4043   0.10111   0.09418  -0.0267   1.0000   0.1231
  -8.000  -0.4147   0.09896   0.09216  -0.0282   1.0000   0.1236
  -7.750  -0.3947   0.09397   0.08715  -0.0249   1.0000   0.1273
  -7.500  -0.4147   0.08665   0.07987  -0.0351   1.0000   0.0797
  -7.250  -0.4057   0.08337   0.07663  -0.0321   1.0000   0.0780
  -7.000  -0.4027   0.07993   0.07323  -0.0319   1.0000   0.0758
  -6.750  -0.4016   0.07623   0.06957  -0.0328   1.0000   0.0738
  -6.500  -0.4003   0.07220   0.06555  -0.0344   1.0000   0.0720
  -6.250  -0.3970   0.06836   0.06169  -0.0357   1.0000   0.0718
  -6.000  -0.3916   0.06466   0.05793  -0.0368   1.0000   0.0726
  -5.750  -0.3844   0.06083   0.05400  -0.0379   1.0000   0.0733
  -5.500  -0.3753   0.05676   0.04978  -0.0390   1.0000   0.0731
  -5.250  -0.3641   0.05252   0.04530  -0.0401   1.0000   0.0722
  -5.000  -0.3506   0.04845   0.04093  -0.0409   1.0000   0.0718
  -4.750  -0.3353   0.04485   0.03700  -0.0414   1.0000   0.0721
  -4.500  -0.3185   0.04191   0.03371  -0.0414   1.0000   0.0746
  -4.250  -0.2998   0.03888   0.03021  -0.0415   1.0000   0.0766
  -4.000  -0.2800   0.03613   0.02699  -0.0413   1.0000   0.0772
  -3.750  -0.2590   0.03371   0.02410  -0.0409   1.0000   0.0779
  -3.500  -0.2372   0.03164   0.02152  -0.0403   1.0000   0.0789
  -3.250  -0.2151   0.02991   0.01937  -0.0397   1.0000   0.0802
  -3.000  -0.1950   0.02891   0.01833  -0.0389   1.0000   0.0836
  -2.750  -0.1736   0.02801   0.01725  -0.0382   1.0000   0.0881
  -2.500  -0.1509   0.02698   0.01590  -0.0374   1.0000   0.0914
  -2.250  -0.1167   0.02591   0.01446  -0.0387   0.9954   0.0948
  -2.000  -0.0813   0.02512   0.01362  -0.0405   0.9888   0.0997
  -1.750  -0.0440   0.02446   0.01269  -0.0422   0.9823   0.1080
  -1.500  -0.0057   0.02397   0.01210  -0.0444   0.9757   0.1237
  -1.250   0.0301   0.02341   0.01162  -0.0463   0.9676   0.1516
  -1.000   0.0676   0.02278   0.01126  -0.0485   0.9590   0.2035
  -0.750   0.1081   0.02200   0.01116  -0.0515   0.9491   0.3290
  -0.500   0.1609   0.01980   0.01073  -0.0555   0.9392   1.0000
  -0.250   0.2040   0.01990   0.01042  -0.0582   0.9247   1.0000
   0.000   0.2448   0.01997   0.01020  -0.0605   0.9106   1.0000
   0.250   0.2843   0.02001   0.01001  -0.0624   0.8971   1.0000
   0.500   0.3235   0.02003   0.00985  -0.0643   0.8838   1.0000
   0.750   0.3617   0.02001   0.00970  -0.0658   0.8701   1.0000
   1.000   0.3969   0.01998   0.00957  -0.0667   0.8551   1.0000
   1.250   0.4302   0.01993   0.00944  -0.0672   0.8388   1.0000
   1.500   0.4629   0.01986   0.00931  -0.0674   0.8216   1.0000
   1.750   0.4958   0.01974   0.00913  -0.0675   0.8035   1.0000
   2.000   0.5269   0.01963   0.00899  -0.0673   0.7836   1.0000
   2.250   0.5563   0.01955   0.00887  -0.0667   0.7612   1.0000
   2.500   0.5872   0.01945   0.00872  -0.0663   0.7379   1.0000
   2.750   0.6168   0.01940   0.00862  -0.0656   0.7118   1.0000
   3.000   0.6441   0.01944   0.00860  -0.0647   0.6826   1.0000
   3.250   0.6706   0.01954   0.00863  -0.0636   0.6510   1.0000
   3.500   0.6955   0.01973   0.00872  -0.0623   0.6169   1.0000
   3.750   0.7194   0.01998   0.00887  -0.0610   0.5813   1.0000
   4.000   0.7432   0.02030   0.00904  -0.0597   0.5469   1.0000
   4.250   0.7667   0.02071   0.00931  -0.0584   0.5152   1.0000
   4.500   0.7899   0.02119   0.00965  -0.0573   0.4867   1.0000
   4.750   0.8130   0.02175   0.01008  -0.0562   0.4619   1.0000
   5.000   0.8366   0.02236   0.01061  -0.0553   0.4407   1.0000
   5.250   0.8606   0.02301   0.01118  -0.0545   0.4217   1.0000
   5.500   0.8848   0.02368   0.01186  -0.0538   0.4043   1.0000
   5.750   0.9093   0.02439   0.01258  -0.0532   0.3887   1.0000
   6.000   0.9337   0.02512   0.01336  -0.0526   0.3744   1.0000
   6.250   0.9584   0.02587   0.01414  -0.0520   0.3614   1.0000
   6.500   0.9824   0.02664   0.01503  -0.0514   0.3488   1.0000
   6.750   1.0058   0.02746   0.01601  -0.0507   0.3366   1.0000
   7.000   1.0290   0.02830   0.01700  -0.0499   0.3250   1.0000
   7.250   1.0520   0.02915   0.01794  -0.0491   0.3137   1.0000
   7.500   1.0738   0.02994   0.01881  -0.0481   0.3011   1.0000
   7.750   1.0930   0.03069   0.01970  -0.0468   0.2870   1.0000
   8.000   1.1107   0.03143   0.02062  -0.0453   0.2724   1.0000
   8.250   1.1276   0.03219   0.02156  -0.0437   0.2580   1.0000
   8.500   1.1440   0.03300   0.02256  -0.0420   0.2439   1.0000
   8.750   1.1596   0.03387   0.02363  -0.0403   0.2300   1.0000
   9.000   1.1736   0.03474   0.02469  -0.0384   0.2153   1.0000
   9.250   1.1862   0.03568   0.02584  -0.0364   0.2002   1.0000
   9.500   1.1963   0.03665   0.02693  -0.0341   0.1844   1.0000
   9.750   1.2038   0.03782   0.02824  -0.0316   0.1678   1.0000
  10.000   1.2071   0.03909   0.02968  -0.0289   0.1497   1.0000
  10.250   1.2071   0.04042   0.03109  -0.0259   0.1327   1.0000
  10.500   1.2041   0.04195   0.03262  -0.0228   0.1175   1.0000
  10.750   1.2012   0.04389   0.03459  -0.0203   0.1049   1.0000
  11.000   1.1973   0.04623   0.03697  -0.0181   0.0945   1.0000
  11.250   1.1914   0.04889   0.03961  -0.0164   0.0867   1.0000
  11.500   1.1857   0.05188   0.04270  -0.0150   0.0797   1.0000
  11.750   1.1785   0.05521   0.04613  -0.0142   0.0742   1.0000
  12.000   1.1714   0.05885   0.04994  -0.0137   0.0690   1.0000
  12.250   1.1639   0.06254   0.05365  -0.0138   0.0654   1.0000
  12.500   1.1573   0.06667   0.05796  -0.0140   0.0623   1.0000
  12.750   1.1494   0.07123   0.06278  -0.0148   0.0597   1.0000
  13.000   1.1402   0.07604   0.06778  -0.0160   0.0572   1.0000
  13.250   1.1322   0.08080   0.07267  -0.0175   0.0552   1.0000
  13.500   1.1272   0.08502   0.07688  -0.0186   0.0530   1.0000
  13.750   1.1167   0.09072   0.08276  -0.0208   0.0518   1.0000
  14.000   1.1005   0.09790   0.09021  -0.0244   0.0511   1.0000
  14.250   1.0837   0.10557   0.09813  -0.0284   0.0509   1.0000
  14.500   1.0627   0.11465   0.10742  -0.0335   0.0508   1.0000
  14.750   1.0400   0.12474   0.11766  -0.0392   0.0512   1.0000
  15.000   1.0163   0.13587   0.12884  -0.0455   0.0517   1.0000
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