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GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 9K AIRFOIL (goe09k-il)
Reynolds number: 500,000
Max Cl/Cd: 79.36 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe09k-il-500000.txt
Download as CSV file: xf-goe09k-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5842   0.09487   0.09258   0.0059   1.0000   0.0046
  -7.750  -0.5814   0.09164   0.08940   0.0026   1.0000   0.0050
  -7.500  -0.5801   0.08829   0.08609   0.0000   1.0000   0.0050
  -7.250  -0.5723   0.08425   0.08206  -0.0039   1.0000   0.0050
  -7.000  -0.5635   0.08021   0.07802  -0.0072   1.0000   0.0050
  -6.750  -0.5623   0.07615   0.07396  -0.0070   1.0000   0.0053
  -6.500  -0.5515   0.07207   0.06987  -0.0103   1.0000   0.0054
  -6.250  -0.5391   0.06778   0.06555  -0.0136   1.0000   0.0057
  -6.000  -0.5240   0.06348   0.06121  -0.0169   1.0000   0.0059
  -5.750  -0.5069   0.05904   0.05670  -0.0200   1.0000   0.0062
  -5.500  -0.4880   0.05469   0.05225  -0.0226   1.0000   0.0065
  -5.250  -0.4657   0.05026   0.04768  -0.0248   1.0000   0.0069
  -5.000  -0.4387   0.04590   0.04314  -0.0265   1.0000   0.0072
  -4.750  -0.3936   0.02412   0.02145  -0.0272   1.0000   0.0075
  -4.500  -0.3782   0.02068   0.01789  -0.0276   1.0000   0.0081
  -4.250  -0.3581   0.01745   0.01447  -0.0277   1.0000   0.0087
  -4.000  -0.3351   0.01458   0.01134  -0.0273   1.0000   0.0097
  -3.750  -0.3085   0.01267   0.00901  -0.0259   1.0000   0.0102
  -3.500  -0.2931   0.00940   0.00561  -0.0261   1.0000   0.0113
  -3.250  -0.2696   0.00786   0.00379  -0.0249   1.0000   0.0135
  -3.000  -0.2473   0.00575   0.00131  -0.0239   1.0000   0.0153
  -2.750  -0.2250   0.00470   0.00006  -0.0230   1.0000   0.0185
  -1.750  -0.1364   0.01005   0.00395  -0.0170   1.0000   0.0088
  -1.500  -0.1117   0.00898   0.00277  -0.0159   1.0000   0.0089
  -1.250  -0.0870   0.00814   0.00184  -0.0150   1.0000   0.0119
  -1.000  -0.0621   0.00745   0.00117  -0.0141   1.0000   0.0584
  -0.750  -0.0173   0.00458   0.00108  -0.0187   1.0000   1.0000
  -0.500   0.0061   0.00461   0.00101  -0.0178   1.0000   1.0000
  -0.250   0.0296   0.00464   0.00098  -0.0170   1.0000   1.0000
   0.000   0.0530   0.00469   0.00097  -0.0161   1.0000   1.0000
   0.250   0.0761   0.00475   0.00101  -0.0153   1.0000   1.0000
   0.500   0.0993   0.00482   0.00107  -0.0144   1.0000   1.0000
   0.750   0.1221   0.00490   0.00118  -0.0135   1.0000   1.0000
   1.000   0.1569   0.00497   0.00130  -0.0153   0.9974   1.0000
   1.250   0.2202   0.00490   0.00138  -0.0233   0.9855   1.0000
   1.500   0.2882   0.00818   0.00141  -0.0322   0.0164   1.0000
   1.750   0.3118   0.00897   0.00232  -0.0310   0.0106   1.0000
   2.000   0.3355   0.00975   0.00314  -0.0298   0.0080   1.0000
   2.250   0.3580   0.01121   0.00475  -0.0281   0.0099   1.0000
   3.250   0.4444   0.00560   0.00050  -0.0199   0.0183   1.0000
   3.500   0.4661   0.00691   0.00195  -0.0192   0.0152   1.0000
   3.750   0.4894   0.00866   0.00419  -0.0174   0.0128   1.0000
   4.000   0.5102   0.01055   0.00631  -0.0164   0.0110   1.0000
   4.250   0.5267   0.01415   0.01018  -0.0154   0.0103   1.0000
   4.500   0.5526   0.01637   0.01282  -0.0133   0.0089   1.0000
   4.750   0.5688   0.01966   0.01630  -0.0128   0.0077   1.0000
   5.000   0.5860   0.02418   0.02110  -0.0118   0.0072   1.0000
   5.250   0.6071   0.02828   0.02547  -0.0110   0.0062   1.0000
   5.500   0.6223   0.03285   0.03022  -0.0109   0.0057   1.0000
   5.750   0.6328   0.03751   0.03500  -0.0111   0.0053   1.0000
   6.000   0.6787   0.05688   0.05422  -0.0124   0.0051   1.0000
   6.250   0.6960   0.06155   0.05906  -0.0133   0.0051   1.0000
   6.500   0.7119   0.06643   0.06407  -0.0151   0.0049   1.0000
   6.750   0.7236   0.07128   0.06901  -0.0173   0.0048   1.0000
   7.000   0.7324   0.07613   0.07393  -0.0199   0.0046   1.0000
   7.250   0.7386   0.08081   0.07865  -0.0229   0.0045   1.0000
   7.500   0.7424   0.08532   0.08318  -0.0261   0.0045   1.0000
   7.750   0.7417   0.08951   0.08737  -0.0292   0.0045   1.0000
   8.000   0.7382   0.09358   0.09141  -0.0320   0.0044   1.0000
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