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GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 14K AIRFOIL (goe14k-il)
Reynolds number: 200,000
Max Cl/Cd: 60.78 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe14k-il-200000.txt
Download as CSV file: xf-goe14k-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 14K 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6035   0.09265   0.08949  -0.0346   0.9962   0.0622
  -8.500  -0.6221   0.08652   0.08332  -0.0393   0.9918   0.0630
  -8.250  -0.6497   0.08286   0.07963  -0.0372   0.9893   0.0630
  -8.000  -0.6743   0.07898   0.07568  -0.0346   0.9875   0.0638
  -7.750  -0.6908   0.07365   0.07015  -0.0336   0.9827   0.0650
  -7.500  -0.7175   0.06976   0.06601  -0.0281   0.9825   0.0665
  -6.750  -0.8300   0.04869   0.04366   0.0014   0.9943   0.0419
  -6.500  -0.8355   0.04509   0.03966   0.0070   0.9939   0.0415
  -6.250  -0.8348   0.04187   0.03599   0.0119   0.9920   0.0418
  -6.000  -0.8263   0.03960   0.03322   0.0156   0.9893   0.0432
  -5.750  -0.8135   0.03860   0.03162   0.0191   0.9869   0.0448
  -5.500  -0.8010   0.03510   0.02769   0.0217   0.9853   0.0458
  -5.250  -0.7899   0.03357   0.02602   0.0247   0.9849   0.0470
  -5.000  -0.7761   0.03284   0.02530   0.0269   0.9835   0.0496
  -4.750  -0.7562   0.03173   0.02392   0.0285   0.9797   0.0519
  -4.500  -0.7287   0.03121   0.02301   0.0289   0.9764   0.0547
  -4.250  -0.7000   0.02984   0.02141   0.0285   0.9746   0.0579
  -4.000  -0.6851   0.02905   0.02060   0.0307   0.9740   0.0617
  -3.750  -0.6120   0.02843   0.01964   0.0221   0.9487   0.0680
  -3.500  -0.5858   0.02708   0.01834   0.0220   0.9452   0.0744
  -3.250  -0.5532   0.02675   0.01792   0.0209   0.9417   0.0798
  -3.000  -0.5160   0.02610   0.01726   0.0188   0.9370   0.0859
  -2.750  -0.4985   0.02567   0.01684   0.0206   0.9332   0.0913
  -2.500  -0.4715   0.02538   0.01652   0.0206   0.9301   0.0975
  -2.250  -0.4365   0.02523   0.01641   0.0188   0.9273   0.1053
  -2.000  -0.4151   0.02491   0.01612   0.0199   0.9222   0.1142
  -1.750  -0.3934   0.02469   0.01594   0.0209   0.9186   0.1266
  -1.500  -0.1160   0.02427   0.01910  -0.0350   0.9318   0.9502
  -1.250   0.0039   0.02629   0.02088  -0.0546   0.9359   0.9968
  -1.000   0.0402   0.02649   0.02098  -0.0570   0.9335   1.0000
  -0.750   0.0647   0.02658   0.02098  -0.0569   0.9300   1.0000
  -0.500   0.0940   0.02675   0.02106  -0.0577   0.9277   1.0000
  -0.250   0.1288   0.02699   0.02122  -0.0595   0.9259   1.0000
   0.000   0.1325   0.02699   0.02117  -0.0552   0.9189   1.0000
   0.250   0.1595   0.02714   0.02128  -0.0555   0.9158   1.0000
   0.500   0.1935   0.02731   0.02140  -0.0572   0.9134   1.0000
   0.750   0.2078   0.02738   0.02145  -0.0549   0.9064   1.0000
   1.000   0.2397   0.02738   0.02142  -0.0560   0.9018   1.0000
   1.250   0.2837   0.02734   0.02135  -0.0594   0.8989   1.0000
   1.500   0.2938   0.02743   0.02144  -0.0562   0.8905   1.0000
   1.750   0.3295   0.02737   0.02139  -0.0580   0.8867   1.0000
   2.000   0.3697   0.02733   0.02136  -0.0606   0.8844   1.0000
   2.250   0.3803   0.02742   0.02146  -0.0575   0.8749   1.0000
   2.500   0.4186   0.02726   0.02133  -0.0596   0.8715   1.0000
   2.750   0.4630   0.02690   0.02102  -0.0627   0.8682   1.0000
   3.000   0.4777   0.02688   0.02104  -0.0602   0.8585   1.0000
   3.250   0.5466   0.02545   0.01969  -0.0673   0.8549   1.0000
   3.500   0.5931   0.02388   0.01819  -0.0696   0.8426   1.0000
   3.750   0.6965   0.02034   0.01480  -0.0821   0.8394   1.0000
   4.000   0.7134   0.01990   0.01443  -0.0793   0.8277   1.0000
   4.250   0.7532   0.01865   0.01331  -0.0805   0.8187   1.0000
   5.000   0.8473   0.01567   0.01059  -0.0793   0.7630   1.0000
   5.250   0.8965   0.01475   0.00848  -0.0816   0.5194   1.0000
   5.500   0.8721   0.01605   0.00914  -0.0708   0.4192   1.0000
   5.750   0.8573   0.01728   0.00988  -0.0625   0.3302   1.0000
   6.000   0.8451   0.01871   0.01066  -0.0551   0.2220   1.0000
   6.250   0.8429   0.01999   0.01147  -0.0498   0.1558   1.0000
   6.500   0.8491   0.02092   0.01218  -0.0460   0.1266   1.0000
   6.750   0.8589   0.02168   0.01286  -0.0428   0.1110   1.0000
   7.000   0.8695   0.02245   0.01357  -0.0399   0.0989   1.0000
   7.250   0.8828   0.02310   0.01425  -0.0373   0.0895   1.0000
   7.500   0.8940   0.02403   0.01514  -0.0345   0.0808   1.0000
   7.750   0.9072   0.02485   0.01594  -0.0321   0.0734   1.0000
   8.000   0.9225   0.02578   0.01691  -0.0301   0.0662   1.0000
   8.250   0.9392   0.02675   0.01782  -0.0284   0.0605   1.0000
   8.500   0.9624   0.02783   0.01897  -0.0277   0.0559   1.0000
   8.750   0.9795   0.02854   0.01973  -0.0260   0.0517   1.0000
   9.000   1.0186   0.03037   0.02153  -0.0284   0.0475   1.0000
   9.250   1.0394   0.03129   0.02264  -0.0272   0.0451   1.0000
   9.500   1.0569   0.03218   0.02363  -0.0256   0.0421   1.0000
   9.750   1.0781   0.03329   0.02475  -0.0249   0.0400   1.0000
  10.000   1.1215   0.03631   0.02802  -0.0282   0.0379   1.0000
  10.250   1.1397   0.03823   0.03028  -0.0266   0.0370   1.0000
  10.500   1.1465   0.03952   0.03181  -0.0230   0.0352   1.0000
  10.750   1.1575   0.04152   0.03408  -0.0205   0.0343   1.0000
  11.000   1.1654   0.04305   0.03575  -0.0176   0.0333   1.0000
  11.250   1.1717   0.04478   0.03762  -0.0146   0.0325   1.0000
  11.500   1.1748   0.04705   0.04011  -0.0112   0.0320   1.0000
  11.750   1.1743   0.04957   0.04285  -0.0075   0.0317   1.0000
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