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GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 399 AIRFOIL (goe399-il)
Reynolds number: 50,000
Max Cl/Cd: 40.79 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe399-il-50000.txt
Download as CSV file: xf-goe399-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 399 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3682   0.11271   0.10563  -0.0215   1.0000   0.1267
  -8.750  -0.3736   0.11182   0.10485  -0.0234   1.0000   0.1301
  -8.500  -0.3873   0.11220   0.10540  -0.0256   1.0000   0.1312
  -8.250  -0.3589   0.10411   0.09724  -0.0229   1.0000   0.1381
  -8.000  -0.3613   0.10232   0.09554  -0.0236   1.0000   0.1432
  -7.750  -0.3749   0.10217   0.09556  -0.0249   1.0000   0.1452
  -7.500  -0.3577   0.09650   0.08990  -0.0230   1.0000   0.1519
  -7.250  -0.3646   0.09515   0.08869  -0.0236   1.0000   0.1584
  -7.000  -0.3641   0.09216   0.08580  -0.0239   1.0000   0.1630
  -6.750  -0.3611   0.08960   0.08331  -0.0234   1.0000   0.1723
  -6.250  -0.3602   0.08476   0.07865  -0.0245   1.0000   0.1878
  -5.750  -0.3577   0.07968   0.07371  -0.0258   1.0000   0.2043
  -5.500  -0.3536   0.07672   0.07078  -0.0237   1.0000   0.2165
  -5.250  -0.3499   0.07348   0.06763  -0.0210   1.0000   0.2260
  -5.000  -0.3481   0.07092   0.06512  -0.0202   1.0000   0.2392
  -4.750  -0.3459   0.06846   0.06271  -0.0191   1.0000   0.2553
  -4.500  -0.3438   0.06630   0.06057  -0.0194   1.0000   0.2768
  -4.250  -0.3419   0.06419   0.05850  -0.0177   1.0000   0.3048
  -4.000   0.0458   0.03608   0.02925  -0.0330   1.0000   1.0000
  -3.750   0.0276   0.03614   0.02949  -0.0267   1.0000   0.9882
  -3.500  -0.3463   0.05678   0.05140  -0.0028   1.0000   0.4104
  -3.000  -0.3591   0.05244   0.04728   0.0125   1.0000   0.5142
  -2.750  -0.3671   0.05025   0.04520   0.0206   1.0000   0.5686
  -2.500  -0.3729   0.04790   0.04297   0.0289   1.0000   0.6174
  -2.250  -0.3774   0.04559   0.04075   0.0359   1.0000   0.6624
  -2.000  -0.3800   0.04319   0.03842   0.0426   1.0000   0.7050
  -1.750  -0.0986   0.03575   0.02749  -0.0423   1.0000   0.2147
  -1.500  -0.0696   0.03386   0.02510  -0.0432   1.0000   0.1993
  -1.250  -0.0417   0.03227   0.02295  -0.0435   1.0000   0.1850
  -1.000  -0.0154   0.03102   0.02116  -0.0435   1.0000   0.1762
  -0.750   0.0084   0.03009   0.01985  -0.0432   1.0000   0.1738
  -0.500   0.0300   0.02926   0.01885  -0.0430   1.0000   0.1780
  -0.250   0.0506   0.02877   0.01818  -0.0425   1.0000   0.1848
   0.000   0.0716   0.02841   0.01753  -0.0420   1.0000   0.1876
   0.250   0.1220   0.02809   0.01693  -0.0466   0.9901   0.1981
   0.500   0.1766   0.02787   0.01662  -0.0520   0.9768   0.2297
   0.750   0.2292   0.02728   0.01639  -0.0570   0.9637   0.2983
   1.000   0.2870   0.02574   0.01595  -0.0623   0.9497   1.0000
   1.250   0.3329   0.02660   0.01644  -0.0665   0.9325   1.0000
   1.500   0.3793   0.02740   0.01701  -0.0706   0.9154   1.0000
   1.750   0.4262   0.02810   0.01756  -0.0746   0.8988   1.0000
   2.000   0.4618   0.02876   0.01813  -0.0767   0.8804   1.0000
   2.250   0.4997   0.02937   0.01871  -0.0789   0.8626   1.0000
   2.500   0.5404   0.02989   0.01921  -0.0814   0.8458   1.0000
   2.750   0.5834   0.03029   0.01962  -0.0839   0.8295   1.0000
   3.000   0.6282   0.03054   0.01991  -0.0865   0.8138   1.0000
   3.250   0.6642   0.03087   0.02033  -0.0875   0.7973   1.0000
   3.500   0.6915   0.03143   0.02095  -0.0873   0.7795   1.0000
   3.750   0.7231   0.03183   0.02144  -0.0875   0.7632   1.0000
   4.000   0.7543   0.03222   0.02197  -0.0875   0.7475   1.0000
   4.250   0.7842   0.03265   0.02252  -0.0873   0.7322   1.0000
   4.500   0.8124   0.03316   0.02316  -0.0868   0.7173   1.0000
   4.750   0.8390   0.03377   0.02391  -0.0862   0.7025   1.0000
   5.000   0.8641   0.03447   0.02481  -0.0854   0.6878   1.0000
   5.250   0.8880   0.03527   0.02579  -0.0846   0.6734   1.0000
   5.500   0.9107   0.03617   0.02687  -0.0836   0.6591   1.0000
   5.750   0.9316   0.03724   0.02814  -0.0826   0.6450   1.0000
   6.000   0.9636   0.03703   0.02822  -0.0813   0.6286   1.0000
   6.250   0.9963   0.03573   0.02715  -0.0785   0.6041   1.0000
   6.500   1.0415   0.03224   0.02384  -0.0748   0.5718   1.0000
   6.750   1.0727   0.03015   0.02193  -0.0712   0.5382   1.0000
   7.000   1.0983   0.02838   0.02025  -0.0671   0.4981   1.0000
   7.250   1.1088   0.02718   0.01907  -0.0612   0.4354   1.0000
   7.500   1.0995   0.02741   0.01880  -0.0534   0.3177   1.0000
   7.750   1.0897   0.02995   0.02013  -0.0479   0.2166   1.0000
   8.000   1.0928   0.03259   0.02221  -0.0445   0.1693   1.0000
   8.250   1.1045   0.03516   0.02448  -0.0421   0.1415   1.0000
   8.500   1.1307   0.03821   0.02714  -0.0412   0.1200   1.0000
   8.750   1.1721   0.04204   0.03096  -0.0420   0.1070   1.0000
   9.000   1.1945   0.04497   0.03428  -0.0408   0.0988   1.0000
   9.250   1.2261   0.04989   0.03922  -0.0411   0.0944   1.0000
   9.500   1.2400   0.05354   0.04345  -0.0391   0.0936   1.0000
   9.750   1.2479   0.05733   0.04780  -0.0368   0.0929   1.0000
  10.000   1.2496   0.06115   0.05215  -0.0343   0.0922   1.0000
  10.250   1.2467   0.06514   0.05661  -0.0318   0.0917   1.0000
  10.500   1.2400   0.06925   0.06111  -0.0293   0.0917   1.0000
  10.750   1.2297   0.07351   0.06571  -0.0271   0.0920   1.0000
  11.000   1.2170   0.07789   0.07035  -0.0251   0.0927   1.0000
  11.250   1.2047   0.08251   0.07514  -0.0234   0.0935   1.0000
  11.500   1.1951   0.08750   0.08031  -0.0224   0.0948   1.0000
  11.750   1.1010   0.09384   0.08710  -0.0258   0.1017   1.0000
  12.000   1.0711   0.10197   0.09529  -0.0302   0.1045   1.0000
  12.250   1.0578   0.10932   0.10267  -0.0332   0.1066   1.0000
  12.500   0.9906   0.12878   0.12201  -0.0495   0.1176   1.0000
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