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GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 546 AIRFOIL (goe546-il)
Reynolds number: 200,000
Max Cl/Cd: 80.47 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe546-il-200000.txt
Download as CSV file: xf-goe546-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 546 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3049   0.08817   0.08485  -0.0385   1.0000   0.0613
  -9.000  -0.3180   0.08549   0.08223  -0.0378   1.0000   0.0630
  -8.750  -0.3413   0.08309   0.07992  -0.0374   1.0000   0.0642
  -8.500  -0.3676   0.08084   0.07776  -0.0369   1.0000   0.0647
  -8.250  -0.3914   0.07852   0.07551  -0.0359   1.0000   0.0649
  -8.000  -0.4185   0.07629   0.07335  -0.0346   1.0000   0.0649
  -7.750  -0.4290   0.06655   0.06343  -0.0498   0.9933   0.0652
  -7.500  -0.4020   0.06510   0.06217  -0.0385   0.9940   0.0673
  -7.250  -0.4870   0.06515   0.06168  -0.0523   0.9943   0.0660
  -7.000  -0.4653   0.06329   0.05999  -0.0505   0.9918   0.0675
  -6.750  -0.4418   0.06172   0.05843  -0.0510   0.9881   0.0704
  -6.500  -0.4220   0.05156   0.04750  -0.0653   0.9795   0.0796
  -6.250  -0.3966   0.04880   0.04492  -0.0661   0.9761   0.0818
  -6.000  -0.3660   0.04585   0.04187  -0.0694   0.9728   0.0866
  -5.750  -0.3452   0.04115   0.03670  -0.0728   0.9658   0.0957
  -5.500  -0.3150   0.03107   0.02517  -0.0756   0.9613   0.0671
  -5.250  -0.2790   0.02768   0.02145  -0.0777   0.9591   0.0616
  -5.000  -0.2545   0.02562   0.01903  -0.0774   0.9524   0.0620
  -4.750  -0.2197   0.02374   0.01676  -0.0788   0.9486   0.0628
  -4.500  -0.1816   0.02206   0.01475  -0.0808   0.9461   0.0634
  -4.250  -0.1522   0.02140   0.01384  -0.0810   0.9400   0.0650
  -4.000  -0.1187   0.01956   0.01185  -0.0822   0.9359   0.0668
  -3.750  -0.0803   0.01837   0.01062  -0.0843   0.9330   0.0690
  -3.500  -0.0389   0.01751   0.00975  -0.0869   0.9309   0.0726
  -3.250  -0.0122   0.01699   0.00918  -0.0865   0.9232   0.0761
  -3.000   0.0268   0.01615   0.00831  -0.0886   0.9197   0.0794
  -2.750   0.0689   0.01520   0.00745  -0.0914   0.9174   0.0863
  -2.500   0.1023   0.01457   0.00685  -0.0924   0.9113   0.0968
  -2.250   0.1373   0.01387   0.00623  -0.0936   0.9053   0.1198
  -2.000   0.1709   0.01218   0.00584  -0.0953   0.9014   0.4315
  -1.750   0.1962   0.01188   0.00579  -0.0944   0.8925   0.5220
  -1.500   0.2304   0.01148   0.00558  -0.0953   0.8872   0.5902
  -1.250   0.2565   0.01119   0.00551  -0.0945   0.8790   0.6547
  -1.000   0.2831   0.01069   0.00542  -0.0934   0.8720   0.7608
  -0.750   0.3644   0.01010   0.00518  -0.1032   0.8712   0.9779
  -0.500   0.4064   0.01006   0.00500  -0.1062   0.8628   1.0000
  -0.250   0.4358   0.01000   0.00481  -0.1063   0.8545   1.0000
   0.000   0.4579   0.01005   0.00478  -0.1050   0.8430   1.0000
   0.250   0.4841   0.01006   0.00470  -0.1044   0.8335   1.0000
   0.500   0.5108   0.01006   0.00461  -0.1039   0.8239   1.0000
   0.750   0.5341   0.01012   0.00461  -0.1028   0.8127   1.0000
   1.000   0.5603   0.01013   0.00454  -0.1022   0.8026   1.0000
   1.250   0.5872   0.01011   0.00444  -0.1017   0.7921   1.0000
   1.500   0.6109   0.01013   0.00442  -0.1005   0.7791   1.0000
   1.750   0.6355   0.01015   0.00440  -0.0996   0.7664   1.0000
   2.000   0.6607   0.01017   0.00436  -0.0987   0.7536   1.0000
   2.250   0.6860   0.01020   0.00433  -0.0979   0.7403   1.0000
   2.500   0.7118   0.01025   0.00434  -0.0972   0.7277   1.0000
   2.750   0.7376   0.01033   0.00438  -0.0965   0.7158   1.0000
   3.000   0.7622   0.01044   0.00445  -0.0957   0.7020   1.0000
   3.250   0.7870   0.01053   0.00451  -0.0947   0.6865   1.0000
   3.500   0.8113   0.01065   0.00454  -0.0937   0.6687   1.0000
   3.750   0.8342   0.01079   0.00464  -0.0924   0.6488   1.0000
   4.000   0.8573   0.01096   0.00475  -0.0912   0.6288   1.0000
   4.250   0.8804   0.01117   0.00488  -0.0900   0.6087   1.0000
   4.500   0.9028   0.01137   0.00506  -0.0887   0.5883   1.0000
   4.750   0.9249   0.01156   0.00524  -0.0875   0.5674   1.0000
   5.000   0.9466   0.01178   0.00543  -0.0861   0.5451   1.0000
   5.250   0.9664   0.01201   0.00559  -0.0843   0.5151   1.0000
   5.500   0.9850   0.01231   0.00579  -0.0824   0.4788   1.0000
   5.750   1.0034   0.01269   0.00605  -0.0805   0.4440   1.0000
   6.000   1.0201   0.01319   0.00640  -0.0783   0.4039   1.0000
   6.250   1.0351   0.01379   0.00680  -0.0760   0.3539   1.0000
   6.500   1.0450   0.01471   0.00734  -0.0729   0.2826   1.0000
   6.750   1.0491   0.01611   0.00819  -0.0691   0.1950   1.0000
   7.000   1.0481   0.01805   0.00939  -0.0647   0.0970   1.0000
   7.250   1.0588   0.01915   0.01040  -0.0619   0.0795   1.0000
   7.500   1.0696   0.02009   0.01132  -0.0591   0.0727   1.0000
   7.750   1.0823   0.02085   0.01215  -0.0566   0.0684   1.0000
   8.000   1.0923   0.02179   0.01308  -0.0538   0.0648   1.0000
   8.250   1.1009   0.02289   0.01419  -0.0509   0.0621   1.0000
   8.500   1.1142   0.02376   0.01515  -0.0487   0.0600   1.0000
   8.750   1.1268   0.02475   0.01620  -0.0465   0.0579   1.0000
   9.000   1.1398   0.02578   0.01726  -0.0445   0.0560   1.0000
   9.250   1.1523   0.02701   0.01847  -0.0426   0.0537   1.0000
   9.500   1.1697   0.02864   0.02010  -0.0414   0.0519   1.0000
   9.750   1.1887   0.02979   0.02136  -0.0402   0.0507   1.0000
  10.000   1.2079   0.03100   0.02268  -0.0392   0.0489   1.0000
  10.250   1.2262   0.03225   0.02402  -0.0381   0.0471   1.0000
  10.500   1.2459   0.03367   0.02547  -0.0373   0.0453   1.0000
  10.750   1.2933   0.03749   0.02934  -0.0410   0.0429   1.0000
  11.000   1.3008   0.03861   0.03070  -0.0382   0.0421   1.0000
  11.250   1.3107   0.04019   0.03253  -0.0360   0.0410   1.0000
  11.500   1.3223   0.04228   0.03487  -0.0342   0.0400   1.0000
  11.750   1.3315   0.04464   0.03750  -0.0323   0.0393   1.0000
  12.000   1.3369   0.04697   0.04007  -0.0301   0.0385   1.0000
  12.250   1.3418   0.04920   0.04247  -0.0281   0.0376   1.0000
  12.500   1.3490   0.05127   0.04460  -0.0266   0.0364   1.0000
  12.750   1.3524   0.05457   0.04805  -0.0252   0.0356   1.0000
  13.000   1.3470   0.05905   0.05279  -0.0233   0.0352   1.0000
  13.250   1.3346   0.06291   0.05692  -0.0209   0.0351   1.0000
  13.500   1.3200   0.06658   0.06084  -0.0189   0.0351   1.0000
  13.750   1.3037   0.07029   0.06479  -0.0173   0.0351   1.0000
  14.000   1.2863   0.07412   0.06886  -0.0163   0.0352   1.0000
  14.250   1.2671   0.07818   0.07315  -0.0160   0.0354   1.0000
  14.500   1.2431   0.08297   0.07820  -0.0166   0.0356   1.0000
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