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GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 9K AIRFOIL (goe09k-il)
Reynolds number: 50,000
Max Cl/Cd: 18.71 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe09k-il-50000-n5.txt
Download as CSV file: xf-goe09k-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 9K 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6146   0.11736   0.11037   0.0112   1.0000   0.0735
  -8.750  -0.6168   0.11512   0.10825   0.0082   1.0000   0.0755
  -8.500  -0.6208   0.11318   0.10641   0.0046   1.0000   0.0761
  -8.250  -0.6059   0.10692   0.10010   0.0071   1.0000   0.0799
  -8.000  -0.6043   0.10389   0.09713   0.0055   1.0000   0.0832
  -7.750  -0.6077   0.10189   0.09524   0.0002   1.0000   0.0857
  -7.500  -0.6017   0.09726   0.09067  -0.0009   1.0000   0.0878
  -7.250  -0.5928   0.09294   0.08635   0.0001   1.0000   0.0927
  -7.000  -0.5879   0.09015   0.08358  -0.0065   1.0000   0.0983
  -6.750  -0.5800   0.08549   0.07895  -0.0077   1.0000   0.1014
  -6.500  -0.5704   0.08146   0.07494  -0.0076   1.0000   0.1081
  -6.000  -0.5478   0.07404   0.06739  -0.0165   1.0000   0.1268
  -5.750  -0.5353   0.07011   0.06341  -0.0181   1.0000   0.1402
  -5.250  -0.5102   0.06189   0.05516  -0.0181   1.0000   0.1715
  -4.750  -0.4379   0.05047   0.04276  -0.0270   1.0000   0.0561
  -4.500  -0.4128   0.04623   0.03817  -0.0279   1.0000   0.0444
  -4.250  -0.3868   0.04227   0.03375  -0.0284   1.0000   0.0380
  -4.000  -0.3631   0.03861   0.02974  -0.0285   1.0000   0.0348
  -3.750  -0.3349   0.03535   0.02577  -0.0282   1.0000   0.0314
  -3.500  -0.3104   0.03220   0.02225  -0.0278   1.0000   0.0303
  -3.250  -0.2843   0.02939   0.01891  -0.0271   1.0000   0.0298
  -3.000  -0.2573   0.02688   0.01583  -0.0262   1.0000   0.0306
  -2.750  -0.2301   0.02472   0.01313  -0.0251   1.0000   0.0317
  -2.500  -0.2042   0.02250   0.01066  -0.0242   1.0000   0.0337
  -2.250  -0.1774   0.02080   0.00859  -0.0229   1.0000   0.0384
  -2.000  -0.1511   0.01935   0.00678  -0.0220   1.0000   0.0466
  -1.750  -0.1252   0.01795   0.00523  -0.0212   1.0000   0.0684
  -1.500  -0.0853   0.01345   0.00360  -0.0230   1.0000   1.0000
  -1.250  -0.0611   0.01341   0.00292  -0.0221   1.0000   1.0000
  -1.000  -0.0372   0.01338   0.00234  -0.0212   1.0000   1.0000
  -0.750  -0.0133   0.01337   0.00199  -0.0204   1.0000   1.0000
  -0.500   0.0104   0.01338   0.00174  -0.0197   1.0000   1.0000
  -0.250   0.0341   0.01340   0.00158  -0.0189   1.0000   1.0000
   0.000   0.0578   0.01343   0.00146  -0.0182   1.0000   1.0000
   0.250   0.0814   0.01347   0.00144  -0.0175   1.0000   1.0000
   0.500   0.1050   0.01352   0.00150  -0.0168   1.0000   1.0000
   0.750   0.1284   0.01359   0.00165  -0.0160   1.0000   1.0000
   1.000   0.1519   0.01367   0.00184  -0.0153   1.0000   1.0000
   1.250   0.1752   0.01377   0.00211  -0.0146   1.0000   1.0000
   1.500   0.1986   0.01388   0.00246  -0.0138   1.0000   1.0000
   1.750   0.2219   0.01401   0.00301  -0.0131   1.0000   1.0000
   2.000   0.2452   0.01417   0.00361  -0.0122   1.0000   1.0000
   2.250   0.2685   0.01435   0.00433  -0.0114   1.0000   1.0000
   2.750   0.3901   0.02152   0.00891  -0.0215   0.0365   1.0000
   3.000   0.4187   0.02340   0.01104  -0.0208   0.0326   1.0000
   3.250   0.4481   0.02555   0.01358  -0.0197   0.0299   1.0000
   3.500   0.4765   0.02797   0.01650  -0.0186   0.0285   1.0000
   3.750   0.5039   0.03066   0.01968  -0.0175   0.0289   1.0000
   4.000   0.5298   0.03360   0.02311  -0.0163   0.0297   1.0000
   4.250   0.5542   0.03675   0.02674  -0.0152   0.0305   1.0000
   4.500   0.5769   0.04008   0.03052  -0.0142   0.0312   1.0000
   4.750   0.5977   0.04377   0.03455  -0.0134   0.0320   1.0000
   5.000   0.6216   0.04728   0.03880  -0.0124   0.0357   1.0000
   5.250   0.6403   0.05139   0.04327  -0.0120   0.0382   1.0000
   5.500   0.6603   0.05578   0.04808  -0.0118   0.0453   1.0000
   6.000   0.7241   0.06869   0.06222  -0.0191   0.1785   1.0000
   6.500   0.7408   0.07675   0.07038  -0.0198   0.1445   1.0000
   6.750   0.7465   0.08101   0.07470  -0.0214   0.1326   1.0000
   7.000   0.7599   0.08660   0.08021  -0.0189   0.1271   1.0000
   7.250   0.7569   0.08958   0.08331  -0.0245   0.1177   1.0000
   7.750   0.7594   0.09798   0.09168  -0.0298   0.1074   1.0000
   8.000   0.7635   0.10225   0.09593  -0.0305   0.1031   1.0000
   8.250   0.7748   0.10832   0.10197  -0.0286   0.0997   1.0000
   8.500   0.7619   0.11070   0.10424  -0.0348   0.0980   1.0000
   8.750   0.7577   0.11396   0.10744  -0.0382   0.0941   1.0000
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