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GOE 566 AIRFOIL (goe566-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 566 AIRFOIL (goe566-il)
Reynolds number: 50,000
Max Cl/Cd: 34.44 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe566-il-50000.txt
Download as CSV file: xf-goe566-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 566 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4292   0.10751   0.10036  -0.0162   1.0000   0.2248
  -8.750  -0.4197   0.10347   0.09636  -0.0158   1.0000   0.2325
  -8.500  -0.4379   0.10273   0.09576  -0.0173   1.0000   0.2415
  -8.250  -0.4185   0.09795   0.09098  -0.0158   1.0000   0.2539
  -8.000  -0.4126   0.09456   0.08762  -0.0151   1.0000   0.2647
  -7.750  -0.4115   0.09172   0.08486  -0.0144   1.0000   0.2790
  -7.500  -0.4095   0.08900   0.08220  -0.0131   1.0000   0.2958
  -7.250  -0.4456   0.08896   0.08242  -0.0129   1.0000   0.3029
  -7.000  -0.4187   0.08460   0.07802  -0.0097   1.0000   0.3313
  -6.750  -0.4324   0.08296   0.07654  -0.0075   1.0000   0.3480
  -6.500  -0.4121   0.07925   0.07282  -0.0044   1.0000   0.3757
  -6.250  -0.4032   0.07642   0.07004  -0.0014   1.0000   0.4037
  -6.000  -0.4018   0.07429   0.06799   0.0025   1.0000   0.4362
  -5.750  -0.3753   0.07124   0.06490   0.0068   1.0000   0.4964
  -5.500  -0.3610   0.06915   0.06285   0.0121   1.0000   0.5614
  -5.250  -0.2887   0.06364   0.05712   0.0124   1.0000   0.6569
  -5.000  -0.2077   0.05772   0.05098   0.0094   1.0000   0.7823
  -4.500  -0.1994   0.05326   0.04667   0.0113   1.0000   0.7968
  -4.000  -0.3758   0.04219   0.03416  -0.0254   1.0000   0.1928
  -3.750  -0.3534   0.03877   0.03018  -0.0255   1.0000   0.1741
  -3.500  -0.3304   0.03610   0.02684  -0.0251   1.0000   0.1633
  -3.250  -0.3096   0.03399   0.02438  -0.0242   1.0000   0.1621
  -3.000  -0.2878   0.03221   0.02219  -0.0234   1.0000   0.1630
  -2.750  -0.2652   0.03053   0.02015  -0.0225   1.0000   0.1624
  -2.500  -0.2417   0.02906   0.01835  -0.0217   1.0000   0.1626
  -2.250  -0.2180   0.02783   0.01677  -0.0208   1.0000   0.1644
  -2.000  -0.1950   0.02669   0.01550  -0.0200   1.0000   0.1696
  -1.750  -0.1718   0.02588   0.01454  -0.0192   1.0000   0.1794
  -1.500  -0.1484   0.02496   0.01362  -0.0183   1.0000   0.1888
  -1.250  -0.1232   0.02420   0.01278  -0.0177   1.0000   0.2023
  -1.000  -0.0993   0.02342   0.01207  -0.0170   1.0000   0.2302
  -0.750  -0.0488   0.01933   0.01067  -0.0192   1.0000   1.0000
  -0.500  -0.0305   0.01965   0.01054  -0.0180   1.0000   1.0000
  -0.250  -0.0125   0.02000   0.01057  -0.0170   1.0000   1.0000
   0.000   0.0055   0.02039   0.01071  -0.0161   1.0000   1.0000
   0.250   0.0234   0.02081   0.01092  -0.0153   1.0000   1.0000
   0.500   0.0414   0.02126   0.01120  -0.0146   1.0000   1.0000
   0.750   0.0592   0.02176   0.01153  -0.0139   1.0000   1.0000
   1.000   0.0769   0.02230   0.01195  -0.0133   1.0000   1.0000
   1.250   0.0945   0.02289   0.01243  -0.0128   1.0000   1.0000
   1.500   0.1118   0.02353   0.01298  -0.0124   1.0000   1.0000
   1.750   0.1292   0.02423   0.01361  -0.0121   0.9998   1.0000
   2.000   0.2106   0.02610   0.01543  -0.0236   0.9705   1.0000
   2.250   0.2789   0.02723   0.01656  -0.0319   0.9419   1.0000
   2.500   0.3323   0.02795   0.01732  -0.0371   0.9160   1.0000
   2.750   0.3866   0.02851   0.01797  -0.0419   0.8911   1.0000
   3.000   0.4471   0.02875   0.01835  -0.0472   0.8664   1.0000
   3.250   0.4954   0.02878   0.01855  -0.0501   0.8392   1.0000
   3.500   0.5516   0.02838   0.01835  -0.0535   0.8112   1.0000
   3.750   0.6048   0.02764   0.01781  -0.0556   0.7821   1.0000
   4.000   0.6545   0.02660   0.01699  -0.0564   0.7510   1.0000
   4.250   0.7013   0.02542   0.01595  -0.0562   0.7180   1.0000
   4.500   0.7346   0.02481   0.01543  -0.0545   0.6797   1.0000
   4.750   0.7697   0.02428   0.01486  -0.0530   0.6436   1.0000
   5.000   0.7960   0.02445   0.01501  -0.0512   0.6080   1.0000
   5.250   0.8214   0.02477   0.01527  -0.0495   0.5756   1.0000
   5.500   0.8457   0.02514   0.01562  -0.0478   0.5456   1.0000
   5.750   0.8688   0.02549   0.01591  -0.0459   0.5159   1.0000
   6.000   0.8916   0.02596   0.01631  -0.0441   0.4879   1.0000
   6.250   0.9165   0.02661   0.01691  -0.0428   0.4636   1.0000
   6.500   0.9377   0.02754   0.01792  -0.0413   0.4389   1.0000
   6.750   0.9592   0.02856   0.01897  -0.0398   0.4135   1.0000
   7.000   0.9814   0.02974   0.02014  -0.0383   0.3869   1.0000
   7.250   0.9989   0.03085   0.02128  -0.0361   0.3535   1.0000
   7.500   1.0148   0.03149   0.02166  -0.0335   0.3138   1.0000
   7.750   1.0271   0.03245   0.02254  -0.0307   0.2753   1.0000
   8.000   1.0404   0.03394   0.02390  -0.0282   0.2380   1.0000
   8.250   1.0519   0.03561   0.02544  -0.0254   0.2006   1.0000
   8.500   1.0644   0.03746   0.02727  -0.0228   0.1724   1.0000
   8.750   1.0799   0.03940   0.02921  -0.0209   0.1535   1.0000
   9.000   1.0955   0.04164   0.03157  -0.0191   0.1399   1.0000
   9.250   1.1135   0.04410   0.03409  -0.0177   0.1296   1.0000
   9.500   1.1198   0.04739   0.03792  -0.0152   0.1227   1.0000
   9.750   1.1404   0.05029   0.04070  -0.0145   0.1160   1.0000
  10.000   1.1377   0.05441   0.04545  -0.0117   0.1142   1.0000
  10.250   1.1299   0.05866   0.05023  -0.0089   0.1128   1.0000
  10.500   1.1172   0.06302   0.05499  -0.0063   0.1120   1.0000
  10.750   1.0989   0.06746   0.05975  -0.0038   0.1119   1.0000
  11.000   1.0748   0.07183   0.06434  -0.0014   0.1124   1.0000
  11.250   1.0492   0.07673   0.06940  -0.0003   0.1133   1.0000
  11.500   1.0250   0.08232   0.07510  -0.0008   0.1145   1.0000
  11.750   1.0017   0.08862   0.08147  -0.0025   0.1154   1.0000
  12.000   0.8530   0.12200   0.11459  -0.0294   0.1479   1.0000
  12.250   0.8441   0.12949   0.12203  -0.0328   0.1523   1.0000
  12.500   0.8452   0.13545   0.12799  -0.0345   0.1543   1.0000
  12.750   0.6521   0.15002   0.14300  -0.0413   0.2708   1.0000
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