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GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 9K AIRFOIL (goe09k-il)
Reynolds number: 200,000
Max Cl/Cd: 29.11 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe09k-il-200000-n5.txt
Download as CSV file: xf-goe09k-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5875   0.10039   0.09682   0.0051   1.0000   0.0101
  -8.000  -0.5851   0.09716   0.09363   0.0030   1.0000   0.0101
  -7.750  -0.5837   0.09384   0.09036   0.0007   1.0000   0.0101
  -7.500  -0.5788   0.09017   0.08672  -0.0026   1.0000   0.0102
  -7.250  -0.5765   0.08584   0.08242  -0.0018   1.0000   0.0105
  -7.000  -0.5707   0.08204   0.07863  -0.0036   1.0000   0.0108
  -6.750  -0.5623   0.07805   0.07464  -0.0066   1.0000   0.0111
  -6.500  -0.5516   0.07401   0.07059  -0.0098   1.0000   0.0116
  -6.250  -0.5386   0.06972   0.06626  -0.0133   1.0000   0.0121
  -6.000  -0.5231   0.06545   0.06193  -0.0168   1.0000   0.0126
  -5.750  -0.5021   0.06097   0.05735  -0.0207   1.0000   0.0135
  -5.500  -0.4752   0.05685   0.05302  -0.0243   1.0000   0.0140
  -5.250  -0.4518   0.05293   0.04889  -0.0262   1.0000   0.0142
  -5.000  -0.4436   0.04774   0.04367  -0.0268   1.0000   0.0150
  -4.750  -0.4259   0.04415   0.03995  -0.0274   1.0000   0.0161
  -4.500  -0.4038   0.04060   0.03619  -0.0280   1.0000   0.0174
  -4.250  -0.3719   0.03892   0.03411  -0.0276   1.0000   0.0203
  -4.000  -0.3517   0.03407   0.02892  -0.0277   1.0000   0.0212
  -3.750  -0.3332   0.03011   0.02480  -0.0277   1.0000   0.0228
  -3.250  -0.2818   0.02339   0.01728  -0.0253   1.0000   0.0094
  -3.000  -0.2569   0.02068   0.01417  -0.0242   1.0000   0.0085
  -2.750  -0.2314   0.01840   0.01147  -0.0231   1.0000   0.0085
  -2.500  -0.2056   0.01639   0.00905  -0.0219   1.0000   0.0087
  -2.250  -0.1797   0.01448   0.00678  -0.0207   1.0000   0.0081
  -2.000  -0.1546   0.01296   0.00502  -0.0195   1.0000   0.0081
  -1.750  -0.1302   0.01180   0.00374  -0.0185   1.0000   0.0089
  -1.500  -0.1058   0.01095   0.00280  -0.0177   1.0000   0.0125
  -1.250  -0.0809   0.01027   0.00194  -0.0168   1.0000   0.0212
  -1.000  -0.0374   0.00689   0.00151  -0.0206   1.0000   1.0000
  -0.750  -0.0135   0.00690   0.00130  -0.0198   1.0000   1.0000
  -0.500   0.0103   0.00692   0.00118  -0.0190   1.0000   1.0000
  -0.250   0.0341   0.00695   0.00111  -0.0183   1.0000   1.0000
   0.000   0.0579   0.00698   0.00106  -0.0175   1.0000   1.0000
   0.250   0.0815   0.00703   0.00108  -0.0168   1.0000   1.0000
   0.500   0.1051   0.00709   0.00114  -0.0160   1.0000   1.0000
   0.750   0.1285   0.00716   0.00125  -0.0152   1.0000   1.0000
   1.000   0.1519   0.00724   0.00139  -0.0145   1.0000   1.0000
   1.250   0.1751   0.00733   0.00157  -0.0137   1.0000   1.0000
   1.500   0.2160   0.00742   0.00187  -0.0168   0.9918   1.0000
   1.750   0.3076   0.01099   0.00226  -0.0298   0.0156   1.0000
   2.000   0.3315   0.01183   0.00326  -0.0288   0.0104   1.0000
   2.250   0.3552   0.01276   0.00435  -0.0276   0.0085   1.0000
   2.500   0.3785   0.01409   0.00578  -0.0263   0.0080   1.0000
   2.750   0.4024   0.01593   0.00770  -0.0252   0.0074   1.0000
   3.000   0.4289   0.01743   0.00956  -0.0240   0.0069   1.0000
   3.250   0.4548   0.01955   0.01205  -0.0227   0.0069   1.0000
   3.500   0.4810   0.02203   0.01499  -0.0212   0.0084   1.0000
   3.750   0.5064   0.02529   0.01870  -0.0194   0.0129   1.0000
   6.000   0.6828   0.05917   0.05529  -0.0126   0.0138   1.0000
   6.250   0.7005   0.06358   0.05990  -0.0139   0.0129   1.0000
   6.500   0.7133   0.06815   0.06460  -0.0155   0.0123   1.0000
   6.750   0.7235   0.07276   0.06931  -0.0175   0.0117   1.0000
   7.000   0.7309   0.07733   0.07394  -0.0196   0.0113   1.0000
   7.250   0.7360   0.08169   0.07834  -0.0215   0.0109   1.0000
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