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GOE 113 AIRFOIL (goe113-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 113 AIRFOIL (goe113-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.29 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe113-il-1000000-n5.txt
Download as CSV file: xf-goe113-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 113 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3435   0.08737   0.08589  -0.0150   1.0000   0.0024
  -8.500  -0.3425   0.08356   0.08210  -0.0158   1.0000   0.0024
  -8.250  -0.4483   0.09628   0.09472  -0.0063   1.0000   0.0024
  -8.000  -0.4440   0.09285   0.09131  -0.0080   1.0000   0.0023
  -7.750  -0.4406   0.08933   0.08780  -0.0098   1.0000   0.0023
  -7.500  -0.4385   0.08587   0.08437  -0.0116   1.0000   0.0023
  -7.250  -0.4340   0.08208   0.08060  -0.0146   1.0000   0.0022
  -7.000  -0.4268   0.07785   0.07638  -0.0186   1.0000   0.0022
  -6.750  -0.4194   0.07354   0.07207  -0.0223   1.0000   0.0022
  -6.500  -0.4022   0.06792   0.06643  -0.0288   0.9980   0.0023
  -6.250  -0.3742   0.06100   0.05945  -0.0377   0.9945   0.0025
  -6.000  -0.3454   0.05411   0.05247  -0.0458   0.9899   0.0026
  -5.750  -0.3160   0.04836   0.04659  -0.0519   0.9854   0.0027
  -5.500  -0.2863   0.04407   0.04218  -0.0562   0.9800   0.0029
  -5.250  -0.2574   0.04038   0.03836  -0.0594   0.9730   0.0032
  -5.000  -0.2271   0.03524   0.03301  -0.0624   0.9644   0.0034
  -4.750  -0.1967   0.02764   0.02497  -0.0647   0.9533   0.0033
  -4.500  -0.1703   0.01133   0.00691  -0.0642   0.9417   0.0037
  -4.250  -0.1438   0.01002   0.00531  -0.0639   0.9212   0.0041
  -4.000  -0.1183   0.00942   0.00445  -0.0632   0.8888   0.0044
  -3.750  -0.0931   0.00886   0.00362  -0.0625   0.8495   0.0051
  -3.500  -0.0674   0.00854   0.00308  -0.0620   0.8136   0.0061
  -3.250  -0.0411   0.00835   0.00264  -0.0616   0.7774   0.0071
  -3.000  -0.0142   0.00820   0.00236  -0.0614   0.7453   0.0098
  -2.750   0.0132   0.00836   0.00247  -0.0612   0.7146   0.0127
  -2.500   0.0408   0.00875   0.00277  -0.0611   0.6816   0.0171
  -2.250   0.0684   0.00906   0.00294  -0.0611   0.6496   0.0206
  -2.000   0.0961   0.00931   0.00308  -0.0611   0.6267   0.0222
  -1.750   0.1241   0.00963   0.00331  -0.0611   0.6081   0.0230
  -1.500   0.1514   0.00925   0.00281  -0.0611   0.5898   0.0239
  -1.250   0.1787   0.00883   0.00232  -0.0611   0.5722   0.0255
  -1.000   0.2063   0.00867   0.00207  -0.0611   0.5563   0.0262
  -0.750   0.2341   0.00851   0.00181  -0.0612   0.5408   0.0256
  -0.500   0.2619   0.00840   0.00161  -0.0612   0.5257   0.0252
  -0.250   0.2898   0.00831   0.00145  -0.0612   0.5130   0.0248
   0.000   0.3178   0.00824   0.00132  -0.0613   0.5001   0.0246
   0.250   0.3457   0.00818   0.00121  -0.0614   0.4868   0.0244
   0.500   0.3735   0.00816   0.00111  -0.0614   0.4709   0.0242
   0.750   0.4012   0.00816   0.00103  -0.0614   0.4504   0.0242
   1.000   0.4289   0.00819   0.00096  -0.0615   0.4278   0.0245
   1.250   0.4564   0.00827   0.00091  -0.0615   0.3989   0.0257
   1.500   0.4835   0.00843   0.00093  -0.0615   0.3611   0.0304
   1.750   0.5102   0.00868   0.00101  -0.0614   0.3153   0.0339
   2.000   0.5368   0.00896   0.00113  -0.0614   0.2677   0.0431
   2.500   0.5849   0.00728   0.00152  -0.0607   0.2142   1.0000
   2.750   0.6122   0.00745   0.00163  -0.0607   0.2009   1.0000
   3.000   0.6389   0.00775   0.00177  -0.0607   0.1687   1.0000
   3.250   0.6656   0.00805   0.00193  -0.0606   0.1392   1.0000
   3.500   0.6921   0.00836   0.00212  -0.0606   0.1153   1.0000
   3.750   0.7188   0.00863   0.00230  -0.0605   0.0990   1.0000
   4.000   0.7438   0.00924   0.00267  -0.0602   0.0408   1.0000
   4.250   0.7698   0.00965   0.00299  -0.0600   0.0125   1.0000
   4.500   0.7967   0.00986   0.00325  -0.0599   0.0100   1.0000
   4.750   0.8232   0.01017   0.00359  -0.0598   0.0074   1.0000
   5.000   0.8496   0.01046   0.00391  -0.0596   0.0060   1.0000
   5.250   0.8759   0.01077   0.00427  -0.0594   0.0051   1.0000
   5.500   0.9015   0.01120   0.00475  -0.0591   0.0043   1.0000
   5.750   0.9269   0.01168   0.00531  -0.0588   0.0039   1.0000
   6.000   0.9524   0.01211   0.00579  -0.0585   0.0034   1.0000
   6.250   0.9779   0.01248   0.00620  -0.0582   0.0029   1.0000
   6.500   1.0028   0.01296   0.00673  -0.0579   0.0027   1.0000
   6.750   1.0254   0.01386   0.00774  -0.0571   0.0024   1.0000
   7.000   1.0492   0.01450   0.00846  -0.0565   0.0022   1.0000
   7.250   1.0717   0.01533   0.00941  -0.0558   0.0020   1.0000
   7.500   1.0926   0.01639   0.01059  -0.0547   0.0018   1.0000
   7.750   1.1121   0.01766   0.01199  -0.0534   0.0017   1.0000
   8.000   1.1303   0.01918   0.01366  -0.0519   0.0016   1.0000
   8.250   1.1471   0.02112   0.01577  -0.0501   0.0016   1.0000
   8.500   1.1630   0.02368   0.01857  -0.0481   0.0016   1.0000
   8.750   1.1795   0.02614   0.02125  -0.0463   0.0015   1.0000
   9.000   1.1968   0.02773   0.02301  -0.0451   0.0015   1.0000
   9.250   1.2132   0.02917   0.02461  -0.0438   0.0014   1.0000
   9.500   1.2280   0.03057   0.02617  -0.0425   0.0013   1.0000
   9.750   1.2360   0.03312   0.02897  -0.0404   0.0012   1.0000
  10.000   1.2359   0.03706   0.03327  -0.0373   0.0012   1.0000
  10.250   1.2365   0.04021   0.03668  -0.0345   0.0012   1.0000
  10.500   1.2322   0.04333   0.04004  -0.0313   0.0011   1.0000
  10.750   1.2208   0.04622   0.04313  -0.0275   0.0011   1.0000
  11.000   1.2071   0.04949   0.04659  -0.0248   0.0011   1.0000
  11.250   1.1914   0.05336   0.05066  -0.0236   0.0011   1.0000
  11.500   1.1765   0.05784   0.05531  -0.0241   0.0011   1.0000
  11.750   1.1598   0.06324   0.06088  -0.0261   0.0011   1.0000
  12.000   1.1431   0.06939   0.06719  -0.0295   0.0011   1.0000
  12.250   1.1263   0.07627   0.07422  -0.0339   0.0011   1.0000
  12.500   1.1091   0.08383   0.08190  -0.0390   0.0011   1.0000
  12.750   1.0916   0.09214   0.09033  -0.0445   0.0011   1.0000
  13.000   1.0733   0.10132   0.09961  -0.0507   0.0012   1.0000
  13.250   1.0545   0.11139   0.10977  -0.0570   0.0012   1.0000
  13.750   0.8844   0.10785   0.10624  -0.0369   0.0013   1.0000
  14.000   0.8540   0.11475   0.11323  -0.0395   0.0013   1.0000
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