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GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 5K AIRFOIL (goe05k-il)
Reynolds number: 100,000
Max Cl/Cd: 25.64 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe05k-il-100000.txt
Download as CSV file: xf-goe05k-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 5K 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5298   0.10174   0.09680  -0.0115   1.0000   0.0432
  -8.000  -0.5317   0.09954   0.09468  -0.0137   1.0000   0.0438
  -7.750  -0.5333   0.09724   0.09245  -0.0168   1.0000   0.0442
  -7.500  -0.5289   0.09458   0.08982  -0.0219   1.0000   0.0445
  -7.250  -0.5259   0.08852   0.08380  -0.0165   1.0000   0.0470
  -7.000  -0.5210   0.08499   0.08029  -0.0169   1.0000   0.0494
  -6.750  -0.5151   0.08149   0.07681  -0.0192   1.0000   0.0519
  -6.500  -0.5058   0.07806   0.07336  -0.0232   1.0000   0.0542
  -6.250  -0.4887   0.07550   0.07063  -0.0306   1.0000   0.0558
  -6.000  -0.4847   0.07002   0.06524  -0.0292   1.0000   0.0577
  -5.750  -0.4771   0.06630   0.06155  -0.0279   1.0000   0.0618
  -5.500  -0.4520   0.06431   0.05917  -0.0338   1.0000   0.0678
  -5.250  -0.4462   0.05858   0.05356  -0.0327   1.0000   0.0707
  -5.000  -0.4338   0.05512   0.05005  -0.0323   1.0000   0.0777
  -4.750  -0.4153   0.05141   0.04611  -0.0341   1.0000   0.0851
  -4.500  -0.3954   0.04861   0.04298  -0.0352   1.0000   0.0977
  -4.250  -0.3792   0.04530   0.03952  -0.0351   1.0000   0.1121
  -4.000  -0.3650   0.04152   0.03576  -0.0343   1.0000   0.1281
  -3.750  -0.3484   0.03878   0.03287  -0.0338   1.0000   0.1566
  -2.750  -0.3049   0.02861   0.02322  -0.0222   1.0000   0.3948
  -2.500  -0.2183   0.02529   0.01738  -0.0308   1.0000   0.1388
  -2.250  -0.1831   0.02212   0.01350  -0.0288   1.0000   0.0730
  -2.000  -0.1539   0.02059   0.01137  -0.0269   1.0000   0.0550
  -1.750  -0.1269   0.01841   0.00893  -0.0259   1.0000   0.0491
  -1.500  -0.1009   0.01693   0.00730  -0.0247   1.0000   0.0514
  -1.250  -0.0760   0.01564   0.00592  -0.0235   1.0000   0.0542
  -1.000  -0.0521   0.01446   0.00470  -0.0222   1.0000   0.0681
  -0.750  -0.0008   0.01071   0.00326  -0.0261   1.0000   1.0000
  -0.500   0.0219   0.01078   0.00291  -0.0252   1.0000   1.0000
  -0.250   0.0445   0.01086   0.00274  -0.0243   1.0000   1.0000
   0.000   0.0669   0.01096   0.00265  -0.0234   1.0000   1.0000
   0.250   0.0893   0.01107   0.00263  -0.0226   1.0000   1.0000
   0.500   0.1116   0.01120   0.00265  -0.0218   1.0000   1.0000
   0.750   0.1339   0.01134   0.00274  -0.0210   1.0000   1.0000
   1.000   0.1560   0.01150   0.00289  -0.0203   1.0000   1.0000
   1.250   0.1781   0.01167   0.00310  -0.0195   1.0000   1.0000
   1.500   0.1998   0.01187   0.00336  -0.0187   1.0000   1.0000
   1.750   0.2216   0.01209   0.00368  -0.0180   1.0000   1.0000
   2.000   0.2431   0.01232   0.00406  -0.0172   1.0000   1.0000
   2.250   0.2646   0.01259   0.00459  -0.0164   1.0000   1.0000
   2.500   0.2859   0.01288   0.00512  -0.0157   1.0000   1.0000
   2.750   0.3072   0.01320   0.00578  -0.0149   1.0000   1.0000
   3.000   0.4898   0.01910   0.00886  -0.0385   0.0426   1.0000
   3.250   0.5176   0.02109   0.01097  -0.0375   0.0416   1.0000
   3.500   0.5471   0.02416   0.01424  -0.0366   0.0456   1.0000
   3.750   0.5771   0.02683   0.01739  -0.0350   0.0569   1.0000
   4.000   0.6156   0.02926   0.02083  -0.0321   0.1047   1.0000
   4.250   0.6959   0.03443   0.02885  -0.0363   0.3627   1.0000
   4.500   0.7103   0.03740   0.03178  -0.0331   0.3226   1.0000
   5.000   0.7290   0.04345   0.03767  -0.0266   0.2210   1.0000
   5.250   0.6965   0.02922   0.02397  -0.0208   0.1885   1.0000
   5.500   0.7479   0.04994   0.04416  -0.0225   0.1459   1.0000
   5.750   0.7565   0.05352   0.04790  -0.0211   0.1217   1.0000
   6.000   0.7665   0.05709   0.05163  -0.0201   0.1056   1.0000
   6.250   0.7750   0.06139   0.05605  -0.0192   0.0955   1.0000
   6.500   0.7867   0.06631   0.06086  -0.0182   0.0858   1.0000
   6.750   0.7889   0.06936   0.06438  -0.0186   0.0802   1.0000
   7.000   0.7958   0.07322   0.06833  -0.0182   0.0740   1.0000
   7.250   0.8031   0.08092   0.07583  -0.0174   0.0702   1.0000
   7.500   0.7982   0.08252   0.07782  -0.0192   0.0682   1.0000
   7.750   0.7963   0.08631   0.08171  -0.0212   0.0659   1.0000
   8.000   0.7934   0.09045   0.08589  -0.0228   0.0634   1.0000
   8.250   0.8097   0.09800   0.09327  -0.0186   0.0579   1.0000
   8.500   0.8022   0.10125   0.09661  -0.0205   0.0578   1.0000
   8.750   0.7927   0.10473   0.10011  -0.0227   0.0576   1.0000
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