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GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 6K AIRFOIL (goe06k-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.63 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe06k-il-1000000.txt
Download as CSV file: xf-goe06k-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3368   0.11597   0.11439  -0.0392   0.9956   0.0074
 -11.000  -0.4779   0.12559   0.12396  -0.0219   1.0000   0.0067
 -10.750  -0.4737   0.12148   0.11986  -0.0239   0.9996   0.0066
 -10.500  -0.4627   0.11880   0.11717  -0.0260   0.9990   0.0072
 -10.250  -0.4536   0.11494   0.11330  -0.0288   0.9982   0.0074
 -10.000  -0.4446   0.11094   0.10930  -0.0318   0.9972   0.0076
  -9.750  -0.4356   0.10696   0.10531  -0.0349   0.9963   0.0080
  -9.500  -0.4257   0.10287   0.10123  -0.0383   0.9955   0.0087
  -9.250  -0.4149   0.09861   0.09696  -0.0423   0.9947   0.0091
  -9.000  -0.4061   0.09454   0.09290  -0.0463   0.9925   0.0096
  -8.750  -0.3965   0.09040   0.08876  -0.0501   0.9905   0.0097
  -8.500  -0.3868   0.08600   0.08437  -0.0544   0.9885   0.0097
  -8.250  -0.3757   0.08151   0.07988  -0.0596   0.9868   0.0097
  -8.000  -0.3638   0.07640   0.07477  -0.0670   0.9850   0.0097
  -7.750  -0.3554   0.07157   0.06993  -0.0723   0.9794   0.0097
  -7.500  -0.3386   0.06555   0.06386  -0.0798   0.9759   0.0098
  -7.250  -0.3188   0.05988   0.05812  -0.0864   0.9740   0.0098
  -7.000  -0.2975   0.05365   0.05178  -0.0927   0.9726   0.0098
  -6.750  -0.2611   0.02774   0.02579  -0.0959   0.9630   0.0101
  -5.750  -0.2385   0.02513   0.02200  -0.0952   0.9523   0.0089
  -5.500  -0.2245   0.01835   0.01455  -0.0927   0.9499   0.0094
  -5.000  -0.1727   0.01345   0.00885  -0.0925   0.9480   0.0100
  -4.750  -0.1447   0.01148   0.00660  -0.0929   0.9472   0.0112
  -4.500  -0.1274   0.01100   0.00605  -0.0907   0.9427   0.0118
  -4.250  -0.1008   0.01042   0.00539  -0.0905   0.9404   0.0129
  -4.000  -0.0706   0.00991   0.00481  -0.0911   0.9389   0.0141
  -3.750  -0.0389   0.00943   0.00426  -0.0921   0.9377   0.0148
  -3.500  -0.0092   0.00846   0.00315  -0.0927   0.9363   0.0172
  -3.250   0.0244   0.00818   0.00286  -0.0942   0.9352   0.0198
  -3.000   0.0587   0.00791   0.00256  -0.0958   0.9342   0.0222
  -2.750   0.0788   0.00762   0.00221  -0.0941   0.9298   0.0249
  -2.500   0.1069   0.00742   0.00202  -0.0943   0.9270   0.0315
  -2.250   0.1377   0.00720   0.00182  -0.0951   0.9248   0.0401
  -2.000   0.1709   0.00712   0.00173  -0.0965   0.9229   0.0457
  -1.750   0.2048   0.00689   0.00151  -0.0980   0.9211   0.0571
  -1.500   0.2280   0.00681   0.00141  -0.0971   0.9170   0.0638
  -1.250   0.2545   0.00666   0.00132  -0.0969   0.9135   0.0797
  -1.000   0.2774   0.00595   0.00125  -0.0963   0.9101   0.3071
  -0.750   0.2957   0.00504   0.00124  -0.0947   0.9063   0.6193
  -0.500   0.3005   0.00442   0.00130  -0.0894   0.8997   0.8343
  -0.250   0.4224   0.00437   0.00155  -0.1114   0.9074   0.9577
   0.000   0.4519   0.00449   0.00164  -0.1116   0.8990   0.9720
   0.250   0.4935   0.00455   0.00166  -0.1147   0.8921   0.9770
   0.500   0.5329   0.00467   0.00178  -0.1174   0.8860   0.9849
   0.750   0.5816   0.00472   0.00179  -0.1222   0.8790   0.9889
   1.000   0.6176   0.00476   0.00179  -0.1240   0.8646   0.9932
   1.250   0.6579   0.00474   0.00175  -0.1269   0.8460   0.9968
   1.500   0.6983   0.00473   0.00168  -0.1299   0.8258   1.0000
   1.750   0.7083   0.00488   0.00164  -0.1258   0.7777   1.0000
   2.000   0.7166   0.00514   0.00167  -0.1214   0.7252   1.0000
   2.250   0.7195   0.00558   0.00178  -0.1158   0.6466   1.0000
   2.500   0.7102   0.00659   0.00209  -0.1077   0.4853   1.0000
   2.750   0.7140   0.00740   0.00237  -0.1027   0.3613   1.0000
   3.000   0.7183   0.00827   0.00268  -0.0980   0.2293   1.0000
   3.250   0.7274   0.00900   0.00298  -0.0942   0.1273   1.0000
   3.500   0.7411   0.00953   0.00324  -0.0914   0.0685   1.0000
   3.750   0.7602   0.00978   0.00345  -0.0896   0.0554   1.0000
   4.000   0.7792   0.01003   0.00368  -0.0878   0.0412   1.0000
   4.250   0.7967   0.01040   0.00394  -0.0856   0.0257   1.0000
   4.500   0.8152   0.01071   0.00427  -0.0837   0.0206   1.0000
   4.750   0.8340   0.01100   0.00457  -0.0818   0.0176   1.0000
   5.000   0.8478   0.01169   0.00536  -0.0788   0.0143   1.0000
   5.250   0.8667   0.01199   0.00570  -0.0770   0.0138   1.0000
   5.500   0.8857   0.01230   0.00605  -0.0752   0.0126   1.0000
   5.750   0.9034   0.01272   0.00652  -0.0731   0.0116   1.0000
   6.000   0.9217   0.01310   0.00690  -0.0713   0.0105   1.0000
   6.250   0.9335   0.01409   0.00799  -0.0680   0.0093   1.0000
   6.500   0.9470   0.01552   0.00957  -0.0652   0.0089   1.0000
   6.750   0.9668   0.01592   0.01002  -0.0637   0.0087   1.0000
   7.000   0.9866   0.01663   0.01083  -0.0622   0.0084   1.0000
   7.250   1.0066   0.01726   0.01153  -0.0607   0.0078   1.0000
   7.500   1.0273   0.01827   0.01265  -0.0595   0.0074   1.0000
   7.750   1.0470   0.01902   0.01349  -0.0581   0.0068   1.0000
   8.000   1.0688   0.02073   0.01539  -0.0571   0.0067   1.0000
   8.250   1.0868   0.02151   0.01626  -0.0554   0.0064   1.0000
   8.500   1.1034   0.02258   0.01744  -0.0536   0.0060   1.0000
   8.750   1.1180   0.02487   0.02000  -0.0515   0.0058   1.0000
   9.000   1.1274   0.02779   0.02326  -0.0484   0.0057   1.0000
   9.250   1.1286   0.03131   0.02717  -0.0439   0.0056   1.0000
   9.500   1.1219   0.03514   0.03140  -0.0383   0.0056   1.0000
   9.750   1.1287   0.03681   0.03325  -0.0349   0.0058   1.0000
  10.000   1.1130   0.04032   0.03706  -0.0282   0.0057   1.0000
  10.250   1.1005   0.04325   0.04024  -0.0222   0.0057   1.0000
  10.500   1.0764   0.04715   0.04441  -0.0155   0.0057   1.0000
  10.750   1.0540   0.05104   0.04852  -0.0099   0.0057   1.0000
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