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GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 101 AIRFOIL (goe101-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.73 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe101-il-1000000-n5.txt
Download as CSV file: xf-goe101-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 101 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3708   0.08635   0.08482  -0.0192   1.0000   0.0039
  -7.750  -0.3704   0.08353   0.08203  -0.0197   1.0000   0.0038
  -7.500  -0.3723   0.08052   0.07905  -0.0203   0.9917   0.0038
  -7.250  -0.3491   0.07472   0.07324  -0.0294   0.9774   0.0038
  -6.750  -0.2839   0.05717   0.05550  -0.0577   0.9271   0.0042
  -6.500  -0.2661   0.05201   0.05016  -0.0630   0.8912   0.0044
  -6.250  -0.2486   0.04800   0.04596  -0.0662   0.8581   0.0045
  -6.000  -0.2298   0.04277   0.04049  -0.0697   0.8267   0.0048
  -5.750  -0.2112   0.02995   0.02706  -0.0757   0.8043   0.0057
  -5.500  -0.2009   0.01271   0.00803  -0.0766   0.7888   0.0068
  -5.250  -0.1761   0.01171   0.00679  -0.0761   0.7644   0.0077
  -5.000  -0.1515   0.01048   0.00525  -0.0756   0.7432   0.0088
  -4.750  -0.1258   0.00987   0.00442  -0.0752   0.7242   0.0099
  -4.500  -0.0985   0.00999   0.00451  -0.0750   0.7056   0.0118
  -4.250  -0.0713   0.01008   0.00453  -0.0748   0.6869   0.0133
  -4.000  -0.0442   0.01011   0.00447  -0.0745   0.6684   0.0147
  -3.500   0.0108   0.01064   0.00490  -0.0742   0.6340   0.0171
  -3.250   0.0380   0.01062   0.00476  -0.0741   0.6168   0.0189
  -3.000   0.0652   0.01063   0.00466  -0.0739   0.5996   0.0203
  -2.750   0.0925   0.01070   0.00464  -0.0737   0.5826   0.0211
  -2.500   0.1198   0.01086   0.00471  -0.0735   0.5656   0.0216
  -2.250   0.1459   0.01007   0.00375  -0.0733   0.5501   0.0228
  -2.000   0.1727   0.00976   0.00337  -0.0731   0.5360   0.0240
  -1.750   0.1997   0.00958   0.00312  -0.0729   0.5237   0.0247
  -1.500   0.2268   0.00934   0.00281  -0.0727   0.5131   0.0251
  -1.250   0.2537   0.00912   0.00251  -0.0725   0.5032   0.0253
  -1.000   0.2809   0.00890   0.00224  -0.0723   0.4941   0.0255
  -0.750   0.3080   0.00875   0.00204  -0.0722   0.4857   0.0259
  -0.500   0.3350   0.00860   0.00182  -0.0720   0.4754   0.0259
  -0.250   0.3621   0.00846   0.00160  -0.0718   0.4640   0.0257
   0.000   0.3891   0.00837   0.00143  -0.0716   0.4511   0.0255
   0.250   0.4163   0.00829   0.00130  -0.0714   0.4414   0.0254
   0.500   0.4437   0.00822   0.00119  -0.0713   0.4352   0.0254
   0.750   0.4711   0.00818   0.00111  -0.0712   0.4289   0.0255
   1.000   0.4985   0.00814   0.00104  -0.0710   0.4219   0.0257
   1.250   0.5259   0.00813   0.00100  -0.0709   0.4162   0.0262
   1.500   0.5533   0.00812   0.00098  -0.0708   0.4098   0.0272
   1.750   0.5805   0.00817   0.00098  -0.0706   0.4004   0.0295
   2.000   0.6079   0.00820   0.00100  -0.0705   0.3909   0.0312
   2.250   0.6351   0.00825   0.00104  -0.0704   0.3829   0.0329
   2.500   0.6623   0.00831   0.00108  -0.0703   0.3730   0.0376
   2.750   0.6894   0.00832   0.00116  -0.0702   0.3635   0.0702
   3.250   0.7451   0.00667   0.00151  -0.0710   0.3452   1.0000
   3.500   0.7719   0.00680   0.00160  -0.0708   0.3338   1.0000
   3.750   0.7985   0.00696   0.00171  -0.0706   0.3182   1.0000
   4.000   0.8244   0.00720   0.00185  -0.0703   0.2939   1.0000
   4.250   0.8473   0.00787   0.00219  -0.0696   0.2249   1.0000
   4.500   0.8704   0.00851   0.00255  -0.0690   0.1698   1.0000
   4.750   0.8958   0.00883   0.00278  -0.0687   0.1485   1.0000
   5.000   0.9190   0.00946   0.00316  -0.0681   0.0964   1.0000
   5.250   0.9439   0.00984   0.00345  -0.0677   0.0798   1.0000
   5.500   0.9695   0.01011   0.00371  -0.0674   0.0693   1.0000
   5.750   0.9911   0.01095   0.00428  -0.0666   0.0197   1.0000
   6.000   1.0162   0.01128   0.00461  -0.0662   0.0123   1.0000
   6.250   1.0414   0.01158   0.00495  -0.0658   0.0103   1.0000
   6.500   1.0659   0.01197   0.00536  -0.0653   0.0083   1.0000
   6.750   1.0904   0.01235   0.00578  -0.0649   0.0072   1.0000
   7.000   1.1149   0.01270   0.00616  -0.0644   0.0064   1.0000
   7.250   1.1389   0.01311   0.00661  -0.0639   0.0056   1.0000
   7.500   1.1619   0.01365   0.00719  -0.0632   0.0048   1.0000
   7.750   1.1855   0.01408   0.00767  -0.0627   0.0045   1.0000
   8.000   1.2086   0.01455   0.00819  -0.0621   0.0041   1.0000
   8.250   1.2313   0.01505   0.00875  -0.0614   0.0038   1.0000
   8.500   1.2534   0.01560   0.00934  -0.0606   0.0036   1.0000
   8.750   1.2745   0.01623   0.01003  -0.0598   0.0033   1.0000
   9.000   1.2924   0.01721   0.01113  -0.0584   0.0030   1.0000
   9.250   1.3134   0.01778   0.01176  -0.0576   0.0029   1.0000
   9.500   1.3335   0.01841   0.01247  -0.0566   0.0027   1.0000
   9.750   1.3514   0.01923   0.01338  -0.0554   0.0025   1.0000
  10.000   1.3699   0.01993   0.01416  -0.0542   0.0024   1.0000
  10.250   1.3861   0.02081   0.01512  -0.0528   0.0023   1.0000
  10.500   1.4018   0.02165   0.01604  -0.0513   0.0022   1.0000
  10.750   1.4158   0.02257   0.01705  -0.0496   0.0021   1.0000
  11.000   1.4281   0.02353   0.01809  -0.0477   0.0020   1.0000
  11.250   1.4356   0.02452   0.01917  -0.0450   0.0020   1.0000
  11.500   1.4401   0.02563   0.02041  -0.0421   0.0019   1.0000
  11.750   1.4432   0.02692   0.02179  -0.0393   0.0019   1.0000
  12.000   1.4393   0.02884   0.02385  -0.0363   0.0018   1.0000
  12.250   1.4332   0.03121   0.02637  -0.0338   0.0017   1.0000
  12.500   1.4345   0.03315   0.02844  -0.0323   0.0017   1.0000
  12.750   1.4320   0.03567   0.03110  -0.0311   0.0017   1.0000
  13.000   1.4308   0.03829   0.03386  -0.0305   0.0017   1.0000
  13.250   1.4266   0.04146   0.03717  -0.0302   0.0017   1.0000
  13.500   1.4260   0.04441   0.04026  -0.0303   0.0016   1.0000
  13.750   1.4191   0.04829   0.04430  -0.0308   0.0016   1.0000
  14.000   1.4153   0.05197   0.04811  -0.0316   0.0016   1.0000
  14.250   1.4073   0.05640   0.05270  -0.0328   0.0016   1.0000
  14.500   1.4006   0.06082   0.05726  -0.0342   0.0015   1.0000
  14.750   1.3889   0.06612   0.06271  -0.0361   0.0015   1.0000
  15.000   1.3784   0.07148   0.06822  -0.0382   0.0015   1.0000
  15.250   1.3642   0.07763   0.07453  -0.0408   0.0015   1.0000
  15.500   1.3514   0.08388   0.08093  -0.0436   0.0014   1.0000
  15.750   1.3333   0.09135   0.08856  -0.0471   0.0015   1.0000
  16.000   1.3197   0.09832   0.09568  -0.0506   0.0014   1.0000
  16.250   1.3024   0.10632   0.10382  -0.0548   0.0015   1.0000
  16.500   1.2873   0.11425   0.11189  -0.0591   0.0014   1.0000
  16.750   1.2690   0.12319   0.12097  -0.0640   0.0015   1.0000
  17.000   1.2500   0.13279   0.13071  -0.0694   0.0015   1.0000
  17.250   1.2336   0.14215   0.14020  -0.0748   0.0015   1.0000
  17.500   1.2153   0.15232   0.15049  -0.0807   0.0015   1.0000
  17.750   1.1971   0.16288   0.16117  -0.0869   0.0015   1.0000
  18.000   1.1796   0.17376   0.17216  -0.0933   0.0015   1.0000
  18.250   1.1557   0.18745   0.18596  -0.1010   0.0016   1.0000
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