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GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 549 AIRFOIL (goe549-il)
Reynolds number: 50,000
Max Cl/Cd: 26.37 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe549-il-50000-n5.txt
Download as CSV file: xf-goe549-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 549 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2991   0.10532   0.09895  -0.0480   1.0000   0.0762
  -9.000  -0.2957   0.10329   0.09700  -0.0451   1.0000   0.0752
  -8.750  -0.3042   0.10170   0.09553  -0.0425   1.0000   0.0744
  -8.500  -0.3012   0.09833   0.09221  -0.0446   0.9937   0.0738
  -8.250  -0.2860   0.09352   0.08740  -0.0501   0.9820   0.0726
  -8.000  -0.2747   0.08858   0.08247  -0.0559   0.9683   0.0718
  -7.750  -0.2658   0.08338   0.07727  -0.0622   0.9538   0.0701
  -7.250  -0.2677   0.06536   0.05880  -0.0850   0.9204   0.0641
  -7.000  -0.2529   0.06056   0.05377  -0.0892   0.9088   0.0637
  -6.750  -0.2374   0.05550   0.04833  -0.0935   0.8983   0.0636
  -6.500  -0.2260   0.05103   0.04329  -0.0959   0.8854   0.0644
  -6.250  -0.2063   0.04867   0.04089  -0.0966   0.8739   0.0660
  -6.000  -0.1851   0.04585   0.03776  -0.0978   0.8641   0.0672
  -5.750  -0.1639   0.04284   0.03428  -0.0986   0.8543   0.0676
  -5.500  -0.1450   0.04050   0.03153  -0.0984   0.8431   0.0681
  -5.250  -0.1176   0.03821   0.02881  -0.0992   0.8357   0.0696
  -5.000  -0.0975   0.03670   0.02695  -0.0984   0.8249   0.0723
  -4.750  -0.0725   0.03508   0.02487  -0.0982   0.8163   0.0746
  -4.500  -0.0462   0.03358   0.02294  -0.0979   0.8079   0.0760
  -4.250  -0.0214   0.03235   0.02154  -0.0975   0.7995   0.0775
  -4.000   0.0056   0.03129   0.02036  -0.0973   0.7920   0.0796
  -3.750   0.0304   0.03051   0.01943  -0.0967   0.7839   0.0829
  -3.500   0.0571   0.02980   0.01850  -0.0963   0.7764   0.0880
  -3.250   0.0822   0.02912   0.01775  -0.0957   0.7691   0.0927
  -3.000   0.1072   0.02853   0.01705  -0.0951   0.7614   0.0980
  -2.750   0.1357   0.02792   0.01625  -0.0950   0.7551   0.1054
  -2.500   0.1575   0.02747   0.01578  -0.0942   0.7469   0.1167
  -2.250   0.1874   0.02653   0.01494  -0.0945   0.7418   0.1506
  -2.000   0.2045   0.02579   0.01490  -0.0935   0.7329   0.2679
  -1.750   0.2280   0.02499   0.01483  -0.0924   0.7275   0.4562
  -1.500   0.2416   0.02487   0.01518  -0.0895   0.7195   0.5965
  -1.250   0.2613   0.02437   0.01517  -0.0863   0.7137   0.7401
  -1.000   0.3623   0.02365   0.01450  -0.0980   0.7092   0.9977
  -0.750   0.3781   0.02400   0.01456  -0.0967   0.7008   1.0000
  -0.500   0.4060   0.02400   0.01421  -0.0967   0.6956   1.0000
  -0.250   0.4203   0.02453   0.01454  -0.0950   0.6866   1.0000
   0.000   0.4489   0.02458   0.01430  -0.0950   0.6811   1.0000
   0.250   0.4658   0.02510   0.01464  -0.0935   0.6726   1.0000
   0.500   0.4936   0.02522   0.01453  -0.0934   0.6667   1.0000
   0.750   0.5131   0.02569   0.01484  -0.0922   0.6589   1.0000
   1.000   0.5387   0.02593   0.01490  -0.0918   0.6524   1.0000
   1.250   0.5622   0.02629   0.01509  -0.0911   0.6455   1.0000
   1.500   0.5839   0.02672   0.01540  -0.0902   0.6380   1.0000
   1.750   0.6152   0.02677   0.01526  -0.0904   0.6330   1.0000
   2.000   0.6287   0.02758   0.01604  -0.0886   0.6236   1.0000
   2.250   0.6597   0.02766   0.01596  -0.0888   0.6184   1.0000
   2.500   0.6731   0.02851   0.01678  -0.0870   0.6092   1.0000
   2.750   0.7018   0.02870   0.01687  -0.0869   0.6035   1.0000
   3.000   0.7170   0.02950   0.01765  -0.0853   0.5950   1.0000
   3.250   0.7426   0.02983   0.01789  -0.0849   0.5885   1.0000
   3.500   0.7605   0.03053   0.01859  -0.0836   0.5808   1.0000
   3.750   0.7815   0.03107   0.01909  -0.0827   0.5734   1.0000
   4.000   0.8041   0.03155   0.01954  -0.0819   0.5667   1.0000
   4.250   0.8187   0.03240   0.02040  -0.0804   0.5583   1.0000
   4.500   0.8527   0.03234   0.02028  -0.0808   0.5538   1.0000
   4.750   0.8535   0.03386   0.02188  -0.0778   0.5431   1.0000
   5.000   0.8871   0.03377   0.02175  -0.0782   0.5386   1.0000
   5.500   0.9181   0.03541   0.02346  -0.0752   0.5235   1.0000
   5.750   0.9133   0.03730   0.02544  -0.0719   0.5129   1.0000
   6.000   0.9459   0.03721   0.02535  -0.0721   0.5085   1.0000
   6.250   0.9362   0.03942   0.02763  -0.0684   0.4979   1.0000
   6.500   0.9682   0.03936   0.02761  -0.0685   0.4936   1.0000
   6.750   0.9505   0.04200   0.03032  -0.0643   0.4828   1.0000
   7.000   0.9822   0.04191   0.03026  -0.0643   0.4787   1.0000
   7.250   0.9601   0.04527   0.03368  -0.0605   0.4675   1.0000
   7.500   0.9908   0.04513   0.03359  -0.0603   0.4637   1.0000
   8.000   0.9962   0.04907   0.03768  -0.0570   0.4485   1.0000
   8.500   0.9986   0.05382   0.04256  -0.0546   0.4332   1.0000
   9.000   0.9981   0.05944   0.04832  -0.0529   0.4179   1.0000
   9.500   0.9966   0.06569   0.05474  -0.0519   0.4026   1.0000
   9.750   0.9684   0.07239   0.06147  -0.0522   0.3907   1.0000
  10.000   0.9922   0.07266   0.06187  -0.0515   0.3877   1.0000
  10.500   0.9848   0.08020   0.06957  -0.0514   0.3731   1.0000
  10.750   1.0110   0.08024   0.06972  -0.0507   0.3709   1.0000
  11.000   0.9766   0.08807   0.07760  -0.0518   0.3591   1.0000
  11.250   1.0013   0.08828   0.07795  -0.0511   0.3564   1.0000
  11.500   0.9700   0.09598   0.08569  -0.0526   0.3461   1.0000
  11.750   0.9885   0.09704   0.08690  -0.0521   0.3424   1.0000
  12.250   0.9824   0.10493   0.09499  -0.0531   0.3288   1.0000
  12.500   1.0125   0.10407   0.09430  -0.0518   0.3256   1.0000
  13.000   1.0262   0.10824   0.09874  -0.0514   0.3103   1.0000
  13.250   1.0078   0.11394   0.10448  -0.0528   0.2985   1.0000
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