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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.47 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802a-il-50000.txt
Download as CSV file: xf-goe802a-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3259   0.10883   0.10192  -0.0256   1.0000   0.0921
  -8.500  -0.3282   0.10672   0.09990  -0.0273   1.0000   0.0930
  -8.250  -0.3275   0.10397   0.09724  -0.0280   1.0000   0.0938
  -8.000  -0.3224   0.10075   0.09407  -0.0277   1.0000   0.0952
  -7.750  -0.3228   0.09823   0.09165  -0.0283   1.0000   0.0965
  -7.500  -0.3255   0.09597   0.08949  -0.0295   1.0000   0.0975
  -7.250  -0.3300   0.09396   0.08756  -0.0309   1.0000   0.0981
  -7.000  -0.3294   0.09117   0.08485  -0.0301   1.0000   0.0989
  -6.750  -0.3292   0.08858   0.08233  -0.0291   1.0000   0.1002
  -6.500  -0.3307   0.08626   0.08005  -0.0289   1.0000   0.1016
  -6.250  -0.3320   0.08402   0.07783  -0.0299   1.0000   0.1028
  -6.000  -0.3305   0.08142   0.07525  -0.0299   1.0000   0.1038
  -5.750  -0.3277   0.07875   0.07262  -0.0290   1.0000   0.1056
  -5.500  -0.3229   0.07621   0.07003  -0.0302   1.0000   0.1077
  -5.250  -0.3169   0.07343   0.06724  -0.0304   1.0000   0.1094
  -5.000  -0.3089   0.07075   0.06448  -0.0312   1.0000   0.1127
  -4.750  -0.3009   0.06795   0.06168  -0.0312   1.0000   0.1159
  -4.500  -0.2910   0.06514   0.05882  -0.0319   1.0000   0.1209
  -4.000  -0.2722   0.06022   0.05388  -0.0320   1.0000   0.1437
  -3.750  -0.2613   0.05828   0.05194  -0.0320   1.0000   0.1593
  -3.500  -0.2481   0.05650   0.05011  -0.0322   1.0000   0.1727
  -3.250  -0.2326   0.05480   0.04833  -0.0330   1.0000   0.1863
  -3.000  -0.2169   0.05308   0.04657  -0.0336   1.0000   0.1997
  -2.750  -0.2004   0.05133   0.04479  -0.0341   1.0000   0.2126
  -2.500  -0.1806   0.04961   0.04297  -0.0355   1.0000   0.2231
  -2.250  -0.1591   0.04810   0.04132  -0.0370   1.0000   0.2282
  -2.000  -0.1112   0.04604   0.03896  -0.0434   0.9926   0.2371
  -1.750  -0.0507   0.04413   0.03671  -0.0515   0.9790   0.2478
  -1.500   0.0104   0.04223   0.03441  -0.0591   0.9652   0.2480
  -1.250   0.0683   0.04044   0.03229  -0.0656   0.9507   0.2450
  -1.000   0.1216   0.03904   0.03052  -0.0709   0.9352   0.2409
  -0.750   0.1727   0.03804   0.02906  -0.0753   0.9195   0.2360
  -0.500   0.2206   0.03726   0.02790  -0.0789   0.9037   0.2329
  -0.250   0.2665   0.03651   0.02686  -0.0820   0.8882   0.2335
   0.000   0.3128   0.03567   0.02583  -0.0849   0.8735   0.2317
   0.250   0.3735   0.03474   0.02448  -0.0890   0.8614   0.2180
   0.500   0.4140   0.03417   0.02378  -0.0904   0.8454   0.2089
   0.750   0.4513   0.03390   0.02332  -0.0911   0.8298   0.2028
   1.000   0.4859   0.03362   0.02304  -0.0917   0.8147   0.2050
   1.250   0.5212   0.03338   0.02280  -0.0923   0.8004   0.2118
   1.500   0.5676   0.03261   0.02205  -0.0939   0.7895   0.2293
   1.750   0.5950   0.03100   0.02228  -0.0933   0.7740   1.0000
   2.000   0.6210   0.03155   0.02253  -0.0923   0.7584   1.0000
   2.250   0.6473   0.03211   0.02285  -0.0915   0.7439   1.0000
   2.500   0.6782   0.03238   0.02291  -0.0911   0.7313   1.0000
   2.750   0.7104   0.03249   0.02286  -0.0907   0.7194   1.0000
   3.000   0.7294   0.03352   0.02380  -0.0897   0.7046   1.0000
   3.250   0.7509   0.03440   0.02462  -0.0888   0.6911   1.0000
   3.500   0.7903   0.03390   0.02400  -0.0887   0.6825   1.0000
   3.750   0.8050   0.03531   0.02540  -0.0875   0.6677   1.0000
   4.000   0.8218   0.03664   0.02672  -0.0865   0.6542   1.0000
   4.250   0.8522   0.03677   0.02681  -0.0858   0.6436   1.0000
   4.500   0.8787   0.03709   0.02712  -0.0848   0.6311   1.0000
   4.750   0.8959   0.03817   0.02821  -0.0834   0.6163   1.0000
   5.000   0.9179   0.03881   0.02885  -0.0821   0.6025   1.0000
   5.250   0.9532   0.03815   0.02817  -0.0810   0.5907   1.0000
   5.500   0.9798   0.03832   0.02834  -0.0798   0.5773   1.0000
   5.750   0.9946   0.03967   0.02975  -0.0784   0.5624   1.0000
   6.000   1.0133   0.04069   0.03083  -0.0770   0.5484   1.0000
   6.250   1.0433   0.04058   0.03075  -0.0758   0.5355   1.0000
   6.500   1.0776   0.04005   0.03018  -0.0748   0.5224   1.0000
   6.750   1.0927   0.04135   0.03158  -0.0732   0.5066   1.0000
   7.000   1.1088   0.04253   0.03289  -0.0715   0.4907   1.0000
   7.250   1.1267   0.04359   0.03403  -0.0699   0.4750   1.0000
   7.500   1.1474   0.04433   0.03483  -0.0683   0.4590   1.0000
   7.750   1.1696   0.04497   0.03551  -0.0668   0.4432   1.0000
   8.000   1.1939   0.04551   0.03608  -0.0655   0.4280   1.0000
   8.250   1.2217   0.04568   0.03628  -0.0642   0.4125   1.0000
   8.500   1.2524   0.04559   0.03612  -0.0632   0.3969   1.0000
   8.750   1.2573   0.04782   0.03856  -0.0610   0.3820   1.0000
   9.000   1.2573   0.05052   0.04146  -0.0587   0.3682   1.0000
   9.250   1.2701   0.05187   0.04292  -0.0568   0.3540   1.0000
   9.500   1.2944   0.05211   0.04317  -0.0554   0.3397   1.0000
   9.750   1.3275   0.05170   0.04269  -0.0545   0.3254   1.0000
  10.000   1.3041   0.05641   0.04773  -0.0513   0.3164   1.0000
  10.250   1.3183   0.05790   0.04929  -0.0497   0.3057   1.0000
  10.500   0.9992   0.10528   0.09654  -0.0631   0.3213   1.0000
  10.750   1.0419   0.10230   0.09372  -0.0591   0.3082   1.0000
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