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GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 286 AIRFOIL (goe286-il)
Reynolds number: 50,000
Max Cl/Cd: 27.89 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe286-il-50000.txt
Download as CSV file: xf-goe286-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3927   0.10839   0.10181  -0.0142   1.0000   0.1786
  -8.000  -0.3697   0.10241   0.09582  -0.0123   1.0000   0.1851
  -7.750  -0.3748   0.10070   0.09422  -0.0140   1.0000   0.1930
  -7.500  -0.3652   0.09668   0.09025  -0.0136   1.0000   0.2000
  -7.250  -0.3722   0.09522   0.08891  -0.0163   1.0000   0.2094
  -7.000  -0.3581   0.09093   0.08465  -0.0142   1.0000   0.2192
  -6.500  -0.3621   0.08662   0.08052  -0.0185   1.0000   0.2415
  -6.250  -0.3487   0.08253   0.07650  -0.0150   1.0000   0.2524
  -6.000  -0.3465   0.07978   0.07384  -0.0145   1.0000   0.2648
  -5.750  -0.3457   0.07727   0.07142  -0.0137   1.0000   0.2795
  -5.500  -0.3440   0.07480   0.06905  -0.0121   1.0000   0.2960
  -5.250  -0.3427   0.07248   0.06682  -0.0100   1.0000   0.3150
  -5.000  -0.3477   0.07070   0.06511  -0.0093   1.0000   0.3391
  -4.750  -0.3438   0.06814   0.06266  -0.0041   1.0000   0.3635
  -4.500  -0.3457   0.06605   0.06069   0.0002   1.0000   0.3936
  -4.250   0.0599   0.04160   0.03520  -0.0228   1.0000   1.0000
  -4.000   0.0720   0.03975   0.03341  -0.0240   1.0000   1.0000
  -3.750   0.0719   0.03872   0.03249  -0.0224   1.0000   0.9952
  -3.500   0.0059   0.04132   0.03538  -0.0066   1.0000   0.9511
  -3.250  -0.0509   0.04281   0.03716   0.0055   1.0000   0.9111
  -3.000  -0.1041   0.04378   0.03841   0.0161   1.0000   0.8806
  -2.750  -0.1613   0.04481   0.03971   0.0272   1.0000   0.8623
  -2.500  -0.2231   0.04576   0.04091   0.0384   1.0000   0.8459
  -2.250  -0.3191   0.04735   0.04281   0.0537   1.0000   0.8117
  -2.000  -0.3673   0.04670   0.04232   0.0578   1.0000   0.7793
  -1.750  -0.0398   0.03626   0.02746  -0.0509   0.9870   0.1744
  -1.500   0.0261   0.03439   0.02481  -0.0579   0.9730   0.1619
  -1.250   0.0874   0.03295   0.02290  -0.0641   0.9578   0.1627
  -1.000   0.1432   0.03159   0.02125  -0.0692   0.9414   0.1654
  -0.750   0.1936   0.03049   0.02001  -0.0730   0.9235   0.1696
  -0.500   0.2478   0.02959   0.01884  -0.0769   0.9059   0.1798
  -0.250   0.3023   0.02840   0.01773  -0.0810   0.8889   0.2080
   0.000   0.3519   0.02622   0.01658  -0.0842   0.8727   0.3441
   0.250   0.4016   0.02442   0.01547  -0.0854   0.8554   1.0000
   0.500   0.4450   0.02432   0.01503  -0.0869   0.8370   1.0000
   0.750   0.4744   0.02458   0.01507  -0.0865   0.8146   1.0000
   1.000   0.5067   0.02471   0.01499  -0.0863   0.7951   1.0000
   1.250   0.5375   0.02484   0.01494  -0.0857   0.7766   1.0000
   1.500   0.5665   0.02501   0.01495  -0.0848   0.7590   1.0000
   1.750   0.5906   0.02553   0.01536  -0.0837   0.7397   1.0000
   2.000   0.6158   0.02600   0.01571  -0.0828   0.7225   1.0000
   2.250   0.6413   0.02646   0.01608  -0.0819   0.7065   1.0000
   2.500   0.6667   0.02694   0.01647  -0.0810   0.6914   1.0000
   2.750   0.6920   0.02742   0.01686  -0.0800   0.6770   1.0000
   3.000   0.7174   0.02787   0.01723  -0.0789   0.6630   1.0000
   3.250   0.7436   0.02823   0.01751  -0.0778   0.6499   1.0000
   3.500   0.7683   0.02879   0.01801  -0.0768   0.6363   1.0000
   3.750   0.7913   0.02958   0.01878  -0.0760   0.6223   1.0000
   4.000   0.8138   0.03045   0.01969  -0.0752   0.6089   1.0000
   4.250   0.8364   0.03140   0.02066  -0.0745   0.5969   1.0000
   4.500   0.8630   0.03192   0.02114  -0.0737   0.5875   1.0000
   4.750   0.8833   0.03320   0.02252  -0.0733   0.5759   1.0000
   5.000   0.9030   0.03456   0.02400  -0.0728   0.5649   1.0000
   5.250   0.9310   0.03493   0.02434  -0.0719   0.5566   1.0000
   5.500   0.9471   0.03667   0.02626  -0.0715   0.5452   1.0000
   5.750   0.9656   0.03813   0.02784  -0.0709   0.5350   1.0000
   6.000   0.9957   0.03813   0.02787  -0.0698   0.5262   1.0000
   6.250   1.0104   0.03978   0.02969  -0.0690   0.5137   1.0000
   6.500   1.0280   0.04102   0.03107  -0.0679   0.5014   1.0000
   6.750   1.0491   0.04197   0.03214  -0.0669   0.4906   1.0000
   7.000   1.0819   0.04152   0.03173  -0.0656   0.4806   1.0000
   7.250   1.0988   0.04269   0.03307  -0.0643   0.4669   1.0000
   7.500   1.1208   0.04311   0.03361  -0.0628   0.4522   1.0000
   7.750   1.1480   0.04277   0.03335  -0.0611   0.4363   1.0000
   8.000   1.1770   0.04220   0.03278  -0.0594   0.4196   1.0000
   8.250   1.1962   0.04289   0.03359  -0.0577   0.4021   1.0000
   8.500   1.2129   0.04405   0.03490  -0.0561   0.3851   1.0000
   8.750   1.2300   0.04527   0.03629  -0.0545   0.3687   1.0000
   9.000   1.2476   0.04646   0.03760  -0.0530   0.3534   1.0000
   9.250   1.2676   0.04746   0.03869  -0.0516   0.3394   1.0000
   9.500   1.2940   0.04789   0.03916  -0.0505   0.3264   1.0000
   9.750   1.2846   0.05194   0.04362  -0.0484   0.3157   1.0000
  10.000   1.2860   0.05476   0.04669  -0.0466   0.3055   1.0000
  10.250   1.3085   0.05525   0.04729  -0.0451   0.2934   1.0000
  10.500   1.3307   0.05542   0.04757  -0.0435   0.2796   1.0000
  10.750   1.2820   0.06313   0.05561  -0.0410   0.2762   1.0000
  11.000   1.3578   0.05697   0.04938  -0.0393   0.2504   1.0000
  11.250   1.3111   0.06396   0.05669  -0.0365   0.2481   1.0000
  11.500   1.2476   0.07382   0.06662  -0.0362   0.2502   1.0000
  11.750   1.3078   0.06846   0.06142  -0.0321   0.2253   1.0000
  12.000   1.3892   0.05712   0.04939  -0.0282   0.1789   1.0000
  12.250   1.3075   0.07117   0.06421  -0.0283   0.1983   1.0000
  12.500   1.2770   0.07822   0.07137  -0.0293   0.1963   1.0000
  13.000   1.3745   0.06785   0.05995  -0.0203   0.1291   1.0000
  13.250   1.3348   0.07460   0.06721  -0.0210   0.1323   1.0000
  13.500   1.2924   0.08340   0.07639  -0.0241   0.1370   1.0000
  13.750   1.2553   0.09286   0.08605  -0.0281   0.1396   1.0000
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