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GOE 559 AIRFOIL (goe559-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 559 AIRFOIL (goe559-il)
Reynolds number: 500,000
Max Cl/Cd: 66.32 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe559-il-500000.txt
Download as CSV file: xf-goe559-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 559 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2387   0.08459   0.08275  -0.0400   1.0000   0.0030
  -8.750  -0.2396   0.08126   0.07944  -0.0403   1.0000   0.0030
  -8.500  -0.2414   0.07787   0.07608  -0.0405   1.0000   0.0030
  -8.250  -0.2366   0.07349   0.07172  -0.0432   0.9946   0.0031
  -8.000  -0.2295   0.06869   0.06693  -0.0467   0.9860   0.0032
  -7.750  -0.2198   0.06368   0.06191  -0.0512   0.9756   0.0032
  -7.500  -0.2083   0.05800   0.05622  -0.0572   0.9603   0.0032
  -7.250  -0.1927   0.05193   0.05012  -0.0653   0.9381   0.0033
  -7.000  -0.1868   0.04646   0.04454  -0.0733   0.9024   0.0032
  -6.750  -0.1901   0.04260   0.04050  -0.0755   0.8609   0.0033
  -6.500  -0.1913   0.03924   0.03693  -0.0761   0.8141   0.0032
  -6.250  -0.1895   0.03577   0.03320  -0.0763   0.7757   0.0033
  -6.000  -0.1840   0.03258   0.02977  -0.0763   0.7496   0.0034
  -5.750  -0.1748   0.02943   0.02639  -0.0760   0.7298   0.0034
  -5.500  -0.1622   0.02648   0.02320  -0.0754   0.7136   0.0035
  -5.250  -0.1481   0.02376   0.02021  -0.0745   0.6989   0.0036
  -5.000  -0.1324   0.02121   0.01740  -0.0733   0.6848   0.0036
  -4.750  -0.1164   0.01865   0.01458  -0.0722   0.6708   0.0036
  -4.500  -0.1072   0.01454   0.01029  -0.0716   0.6581   0.0039
  -4.250  -0.0935   0.01176   0.00730  -0.0708   0.6441   0.0042
  -4.000  -0.0749   0.00986   0.00513  -0.0698   0.6300   0.0045
  -3.750  -0.0514   0.00873   0.00371  -0.0684   0.6158   0.0060
  -3.500  -0.0242   0.00867   0.00325  -0.0666   0.6013   0.0066
  -3.250  -0.0064   0.00632   0.00058  -0.0655   0.5911   0.0070
  -3.000  -0.0360   0.14401   0.14018  -0.0445   0.5770   0.0122
  -1.750   0.1425   0.01431   0.00683  -0.0649   0.5481   0.0160
  -1.500   0.1690   0.01430   0.00655  -0.0642   0.5410   0.0217
  -0.500   0.2670   0.01087   0.00287  -0.0610   0.5183   0.0163
  -0.250   0.2921   0.01061   0.00247  -0.0604   0.5134   0.0099
   0.000   0.3176   0.01034   0.00208  -0.0600   0.5086   0.0084
   0.250   0.3438   0.01022   0.00179  -0.0597   0.5040   0.0097
   0.500   0.3521   0.00835   0.00169  -0.0566   0.5006   0.6552
   0.750   0.4905   0.00797   0.00204  -0.0807   0.4934   1.0000
   1.000   0.5133   0.00801   0.00206  -0.0800   0.4896   1.0000
   1.250   0.5365   0.00809   0.00213  -0.0795   0.4861   1.0000
   1.500   0.5455   0.00880   0.00192  -0.0764   0.3013   1.0000
   1.750   0.5505   0.01053   0.00284  -0.0726   0.0092   1.0000
   2.000   0.5720   0.01076   0.00318  -0.0715   0.0084   1.0000
   2.250   0.5922   0.01112   0.00369  -0.0700   0.0096   1.0000
   2.500   0.6130   0.01144   0.00409  -0.0687   0.0137   1.0000
   2.750   0.6359   0.01161   0.00436  -0.0674   0.0257   1.0000
   3.000   0.6563   0.01202   0.00497  -0.0657   0.0347   1.0000
   3.250   0.6712   0.01281   0.00587  -0.0632   0.0349   1.0000
   3.500   0.6875   0.01347   0.00658  -0.0608   0.0297   1.0000
   3.750   0.6947   0.01466   0.00783  -0.0572   0.0223   1.0000
   4.000   0.7006   0.01595   0.00918  -0.0532   0.0173   1.0000
   4.250   0.7132   0.01691   0.01017  -0.0504   0.0141   1.0000
   4.500   0.7244   0.01896   0.01206  -0.0476   0.0118   1.0000
   4.750   0.7448   0.01958   0.01283  -0.0458   0.0077   1.0000
   5.000   0.7865   0.02446   0.01735  -0.0488   0.0060   1.0000
   5.250   0.8044   0.02430   0.01747  -0.0461   0.0057   1.0000
   5.500   0.8288   0.02465   0.01800  -0.0444   0.0047   1.0000
   5.750   0.8564   0.02655   0.01999  -0.0438   0.0040   1.0000
   6.000   0.8814   0.02932   0.02283  -0.0435   0.0036   1.0000
   6.250   0.9067   0.03441   0.02795  -0.0435   0.0033   1.0000
   6.500   0.9251   0.03572   0.02949  -0.0412   0.0033   1.0000
   6.750   0.9453   0.03632   0.03035  -0.0385   0.0031   1.0000
   7.000   0.9674   0.03767   0.03192  -0.0362   0.0029   1.0000
   7.250   0.9858   0.03988   0.03433  -0.0341   0.0026   1.0000
   7.500   1.0009   0.04234   0.03700  -0.0317   0.0024   1.0000
   7.750   1.0136   0.04490   0.03977  -0.0292   0.0023   1.0000
   8.000   1.0240   0.04765   0.04273  -0.0266   0.0021   1.0000
   8.250   1.0322   0.05033   0.04562  -0.0240   0.0020   1.0000
   8.500   1.0371   0.05325   0.04873  -0.0212   0.0019   1.0000
   8.750   1.0382   0.05636   0.05205  -0.0183   0.0019   1.0000
   9.000   1.0371   0.05946   0.05533  -0.0155   0.0018   1.0000
   9.250   1.0326   0.06272   0.05876  -0.0128   0.0018   1.0000
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