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GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 6K AIRFOIL (goe06k-il)
Reynolds number: 1,000,000
Max Cl/Cd: 132.82 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe06k-il-1000000-n5.txt
Download as CSV file: xf-goe06k-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 6K AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3882   0.12437   0.12262  -0.0456   0.9935   0.0031
 -11.000  -0.3816   0.12041   0.11866  -0.0480   0.9927   0.0032
 -10.750  -0.3745   0.11660   0.11486  -0.0501   0.9919   0.0032
 -10.500  -0.3674   0.11267   0.11093  -0.0523   0.9911   0.0032
 -10.250  -0.3591   0.10885   0.10712  -0.0548   0.9903   0.0032
 -10.000  -0.3509   0.10498   0.10325  -0.0574   0.9896   0.0032
  -9.750  -0.3436   0.10093   0.09921  -0.0600   0.9889   0.0032
  -8.750  -0.3126   0.08623   0.08452  -0.0701   0.9829   0.0032
  -8.500  -0.3045   0.08207   0.08037  -0.0736   0.9812   0.0032
  -8.000  -0.2107   0.05488   0.05327  -0.0838   0.9704   0.0030
  -7.500  -0.2689   0.06520   0.06350  -0.0921   0.9684   0.0029
  -7.250  -0.2641   0.06120   0.05947  -0.0948   0.9601   0.0028
  -7.000  -0.2470   0.05616   0.05437  -0.1005   0.9570   0.0026
  -6.750  -0.2361   0.05112   0.04926  -0.1036   0.9501   0.0025
  -6.500  -0.2180   0.04572   0.04373  -0.1073   0.9454   0.0024
  -6.250  -0.1946   0.03906   0.03685  -0.1116   0.9425   0.0022
  -6.000  -0.1759   0.03474   0.03233  -0.1125   0.9375   0.0024
  -5.750  -0.1552   0.02971   0.02701  -0.1131   0.9329   0.0026
  -5.500  -0.1309   0.02412   0.02102  -0.1137   0.9296   0.0026
  -5.250  -0.1227   0.01438   0.01029  -0.1092   0.9232   0.0029
  -5.000  -0.1007   0.01165   0.00699  -0.1079   0.9191   0.0031
  -4.750  -0.0733   0.01024   0.00526  -0.1079   0.9162   0.0032
  -4.500  -0.0444   0.00935   0.00418  -0.1084   0.9138   0.0033
  -4.250  -0.0195   0.00893   0.00368  -0.1080   0.9105   0.0039
  -4.000   0.0052   0.00853   0.00318  -0.1075   0.9070   0.0043
  -3.750   0.0320   0.00817   0.00272  -0.1074   0.9037   0.0047
  -3.500   0.0603   0.00785   0.00235  -0.1077   0.9008   0.0058
  -3.250   0.0889   0.00758   0.00201  -0.1081   0.8981   0.0067
  -3.000   0.1114   0.00735   0.00175  -0.1070   0.8943   0.0082
  -2.750   0.1366   0.00715   0.00152  -0.1065   0.8909   0.0108
  -2.500   0.1634   0.00698   0.00133  -0.1065   0.8878   0.0154
  -2.250   0.1914   0.00681   0.00118  -0.1067   0.8850   0.0299
  -2.000   0.2169   0.00671   0.00111  -0.1064   0.8818   0.0450
  -1.750   0.2411   0.00661   0.00103  -0.1057   0.8780   0.0544
  -1.500   0.2674   0.00654   0.00093  -0.1055   0.8745   0.0618
  -1.250   0.2942   0.00640   0.00087  -0.1055   0.8714   0.0890
  -1.000   0.3177   0.00609   0.00082  -0.1048   0.8682   0.1934
  -0.750   0.3392   0.00583   0.00080  -0.1036   0.8642   0.2834
  -0.500   0.3607   0.00549   0.00079  -0.1025   0.8601   0.4115
  -0.250   0.3818   0.00508   0.00078  -0.1014   0.8556   0.5679
   0.000   0.3970   0.00474   0.00080  -0.0986   0.8489   0.6931
   0.250   0.4135   0.00443   0.00081  -0.0960   0.8418   0.8081
   0.750   0.5543   0.00447   0.00120  -0.1163   0.8265   0.9769
   1.000   0.5945   0.00462   0.00135  -0.1193   0.8151   0.9870
   1.250   0.6309   0.00475   0.00138  -0.1214   0.7879   0.9908
   1.500   0.6617   0.00503   0.00145  -0.1222   0.7389   0.9957
   1.750   0.6900   0.00529   0.00153  -0.1226   0.6932   0.9985
   2.000   0.7119   0.00562   0.00164  -0.1214   0.6344   1.0000
   2.250   0.7053   0.00657   0.00194  -0.1140   0.4889   1.0000
   2.500   0.7047   0.00755   0.00228  -0.1081   0.3386   1.0000
   2.750   0.7056   0.00859   0.00265  -0.1026   0.1810   1.0000
   3.000   0.7163   0.00924   0.00294  -0.0992   0.0889   1.0000
   3.250   0.7333   0.00958   0.00317  -0.0970   0.0586   1.0000
   3.500   0.7498   0.00998   0.00341  -0.0948   0.0235   1.0000
   3.750   0.7680   0.01029   0.00369  -0.0928   0.0115   1.0000
   4.000   0.7867   0.01056   0.00396  -0.0910   0.0077   1.0000
   4.250   0.8058   0.01082   0.00425  -0.0892   0.0063   1.0000
   4.500   0.8239   0.01117   0.00462  -0.0872   0.0051   1.0000
   4.750   0.8431   0.01143   0.00492  -0.0855   0.0042   1.0000
   5.000   0.8603   0.01185   0.00538  -0.0834   0.0037   1.0000
   5.250   0.8777   0.01222   0.00580  -0.0813   0.0032   1.0000
   5.500   0.8940   0.01265   0.00629  -0.0789   0.0030   1.0000
   5.750   0.9102   0.01309   0.00679  -0.0766   0.0027   1.0000
   6.000   0.9255   0.01364   0.00741  -0.0741   0.0026   1.0000
   6.250   0.9403   0.01433   0.00817  -0.0715   0.0024   1.0000
   6.500   0.9549   0.01528   0.00924  -0.0689   0.0023   1.0000
   6.750   0.9735   0.01578   0.00984  -0.0672   0.0021   1.0000
   7.000   0.9922   0.01680   0.01101  -0.0655   0.0019   1.0000
   7.250   1.0114   0.01724   0.01153  -0.0641   0.0017   1.0000
   7.500   1.0346   0.01882   0.01333  -0.0634   0.0016   1.0000
   7.750   1.0568   0.02001   0.01469  -0.0626   0.0015   1.0000
   8.000   1.0788   0.02198   0.01695  -0.0618   0.0015   1.0000
   8.250   1.0862   0.03163   0.02766  -0.0567   0.0013   1.0000
   8.500   1.0798   0.03845   0.03499  -0.0497   0.0013   1.0000
   8.750   1.0727   0.04350   0.04037  -0.0435   0.0013   1.0000
   9.000   1.0620   0.04840   0.04555  -0.0373   0.0013   1.0000
   9.250   1.0535   0.05191   0.04926  -0.0321   0.0013   1.0000
   9.500   1.0390   0.05536   0.05289  -0.0264   0.0013   1.0000
   9.750   1.0199   0.05878   0.05647  -0.0201   0.0013   1.0000
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