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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 100,000
Max Cl/Cd: 54.47 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe286-il-100000-n5.txt
Download as CSV file: xf-goe286-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 286 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3573   0.09088   0.08624  -0.0217   1.0000   0.0623
  -7.500  -0.3549   0.08790   0.08332  -0.0235   1.0000   0.0640
  -7.250  -0.3515   0.08466   0.08013  -0.0278   1.0000   0.0665
  -7.000  -0.3492   0.08125   0.07667  -0.0386   1.0000   0.0685
  -6.750  -0.3444   0.07788   0.07320  -0.0425   1.0000   0.0688
  -6.500  -0.3420   0.07380   0.06933  -0.0372   1.0000   0.0701
  -6.250  -0.3375   0.07153   0.06714  -0.0341   1.0000   0.0718
  -6.000  -0.3335   0.06907   0.06470  -0.0334   1.0000   0.0735
  -5.750  -0.3104   0.06503   0.06057  -0.0381   0.9947   0.0757
  -5.500  -0.2648   0.05495   0.04995  -0.0516   0.9856   0.0563
  -5.250  -0.2317   0.05031   0.04510  -0.0566   0.9781   0.0559
  -5.000  -0.1967   0.04593   0.04052  -0.0612   0.9714   0.0543
  -4.750  -0.1595   0.04102   0.03524  -0.0659   0.9628   0.0515
  -4.500  -0.1225   0.03590   0.02955  -0.0697   0.9516   0.0494
  -4.250  -0.0887   0.03352   0.02690  -0.0718   0.9379   0.0511
  -4.000  -0.0565   0.03077   0.02374  -0.0732   0.9223   0.0515
  -3.750  -0.0260   0.02810   0.02061  -0.0739   0.9063   0.0508
  -3.500   0.0041   0.02594   0.01802  -0.0743   0.8906   0.0505
  -3.250   0.0339   0.02418   0.01587  -0.0744   0.8750   0.0506
  -3.000   0.0633   0.02274   0.01409  -0.0742   0.8592   0.0509
  -2.750   0.0917   0.02171   0.01282  -0.0739   0.8429   0.0526
  -2.500   0.1197   0.02076   0.01160  -0.0734   0.8265   0.0544
  -2.250   0.1472   0.01983   0.01041  -0.0728   0.8092   0.0551
  -2.000   0.1743   0.01902   0.00941  -0.0721   0.7914   0.0556
  -1.750   0.2012   0.01832   0.00856  -0.0715   0.7732   0.0564
  -1.500   0.2281   0.01773   0.00784  -0.0708   0.7548   0.0572
  -1.250   0.2544   0.01715   0.00723  -0.0703   0.7361   0.0586
  -0.750   0.3071   0.01642   0.00635  -0.0690   0.6969   0.0640
  -0.500   0.3335   0.01621   0.00595  -0.0682   0.6762   0.0691
   0.000   0.3863   0.01580   0.00524  -0.0669   0.6359   0.0847
   0.250   0.4130   0.01557   0.00502  -0.0664   0.6165   0.1173
   0.500   0.4327   0.01376   0.00501  -0.0651   0.5994   0.6883
   1.000   0.4972   0.01359   0.00480  -0.0660   0.5633   1.0000
   1.250   0.5240   0.01376   0.00480  -0.0656   0.5467   1.0000
   1.500   0.5509   0.01393   0.00482  -0.0653   0.5303   1.0000
   1.750   0.5778   0.01411   0.00486  -0.0651   0.5137   1.0000
   2.000   0.6045   0.01430   0.00491  -0.0648   0.4974   1.0000
   2.250   0.6311   0.01451   0.00498  -0.0645   0.4816   1.0000
   2.500   0.6575   0.01474   0.00506  -0.0641   0.4660   1.0000
   2.750   0.6837   0.01500   0.00518  -0.0638   0.4514   1.0000
   3.000   0.7100   0.01527   0.00532  -0.0635   0.4386   1.0000
   3.250   0.7365   0.01554   0.00552  -0.0632   0.4277   1.0000
   3.500   0.7628   0.01584   0.00574  -0.0630   0.4185   1.0000
   3.750   0.7891   0.01613   0.00598  -0.0627   0.4095   1.0000
   4.000   0.8155   0.01644   0.00625  -0.0625   0.4011   1.0000
   4.250   0.8416   0.01675   0.00654  -0.0622   0.3931   1.0000
   4.500   0.8678   0.01707   0.00685  -0.0620   0.3851   1.0000
   4.750   0.8935   0.01740   0.00715  -0.0617   0.3759   1.0000
   5.000   0.9192   0.01772   0.00749  -0.0614   0.3647   1.0000
   5.250   0.9444   0.01805   0.00781  -0.0611   0.3529   1.0000
   5.500   0.9694   0.01840   0.00814  -0.0607   0.3420   1.0000
   5.750   0.9948   0.01873   0.00852  -0.0604   0.3321   1.0000
   6.000   1.0200   0.01908   0.00893  -0.0600   0.3242   1.0000
   6.250   1.0453   0.01943   0.00936  -0.0597   0.3169   1.0000
   6.500   1.0701   0.01980   0.00979  -0.0593   0.3087   1.0000
   6.750   1.0944   0.02018   0.01025  -0.0589   0.2987   1.0000
   7.000   1.1189   0.02056   0.01074  -0.0585   0.2888   1.0000
   7.250   1.1427   0.02098   0.01123  -0.0580   0.2790   1.0000
   7.500   1.1663   0.02141   0.01175  -0.0575   0.2676   1.0000
   7.750   1.1895   0.02186   0.01233  -0.0569   0.2545   1.0000
   8.000   1.2117   0.02238   0.01290  -0.0563   0.2383   1.0000
   8.250   1.2330   0.02296   0.01352  -0.0555   0.2207   1.0000
   8.500   1.2538   0.02359   0.01420  -0.0547   0.2043   1.0000
   8.750   1.2738   0.02428   0.01497  -0.0539   0.1890   1.0000
   9.000   1.2925   0.02508   0.01579  -0.0529   0.1745   1.0000
   9.250   1.3091   0.02602   0.01672  -0.0517   0.1608   1.0000
   9.500   1.3233   0.02712   0.01779  -0.0503   0.1490   1.0000
   9.750   1.3353   0.02836   0.01901  -0.0487   0.1393   1.0000
  10.000   1.3470   0.02957   0.02032  -0.0470   0.1313   1.0000
  10.250   1.3539   0.03104   0.02181  -0.0449   0.1241   1.0000
  10.500   1.3634   0.03220   0.02314  -0.0430   0.1177   1.0000
  10.750   1.3674   0.03366   0.02470  -0.0407   0.1117   1.0000
  11.000   1.3721   0.03518   0.02636  -0.0387   0.1060   1.0000
  11.250   1.3796   0.03662   0.02802  -0.0372   0.0980   1.0000
  11.500   1.3942   0.03760   0.02937  -0.0362   0.0747   1.0000
  11.750   1.3887   0.04028   0.03186  -0.0349   0.0654   1.0000
  12.000   1.3805   0.04355   0.03506  -0.0341   0.0606   1.0000
  12.250   1.3717   0.04716   0.03877  -0.0337   0.0567   1.0000
  12.500   1.3605   0.05138   0.04311  -0.0340   0.0534   1.0000
  12.750   1.3466   0.05627   0.04810  -0.0349   0.0511   1.0000
  13.000   1.3385   0.06058   0.05262  -0.0357   0.0479   1.0000
  13.250   1.3286   0.06528   0.05751  -0.0368   0.0450   1.0000
  13.500   1.3153   0.07053   0.06291  -0.0382   0.0430   1.0000
  13.750   1.3044   0.07560   0.06815  -0.0396   0.0407   1.0000
  14.000   1.2950   0.08056   0.07330  -0.0410   0.0378   1.0000
  14.250   1.2834   0.08598   0.07886  -0.0427   0.0359   1.0000
  14.500   1.2732   0.09133   0.08434  -0.0445   0.0340   1.0000
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