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GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 361 AIRFOIL (goe361-il)
Reynolds number: 500,000
Max Cl/Cd: 103.78 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe361-il-500000.txt
Download as CSV file: xf-goe361-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 361 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2942   0.08862   0.08661  -0.0201   1.0000   0.0169
  -7.000  -0.3010   0.08719   0.08523  -0.0173   1.0000   0.0171
  -6.750  -0.2750   0.08313   0.08116  -0.0230   0.9969   0.0175
  -5.250  -0.0729   0.05489   0.05272  -0.0741   0.9608   0.0217
  -5.000  -0.0409   0.05165   0.04944  -0.0787   0.9546   0.0224
  -4.750  -0.0040   0.04807   0.04579  -0.0850   0.9451   0.0235
  -4.500   0.0463   0.04376   0.04130  -0.0945   0.9331   0.0263
  -4.250   0.0967   0.03955   0.03681  -0.1023   0.9187   0.0269
  -4.000   0.1232   0.03410   0.03117  -0.1061   0.9014   0.0276
  -3.750   0.1463   0.03218   0.02915  -0.1069   0.8817   0.0283
  -3.500   0.1708   0.03036   0.02718  -0.1076   0.8602   0.0291
  -3.250   0.1972   0.02836   0.02496  -0.1084   0.8367   0.0305
  -3.000   0.2311   0.02673   0.02296  -0.1089   0.8111   0.0343
  -2.750   0.2588   0.02250   0.01825  -0.1102   0.7863   0.0356
  -2.500   0.2819   0.02111   0.01671  -0.1101   0.7605   0.0367
  -2.250   0.3065   0.02009   0.01550  -0.1100   0.7376   0.0381
  -2.000   0.3326   0.01899   0.01416  -0.1098   0.7168   0.0404
  -1.750   0.3620   0.01934   0.01414  -0.1089   0.6976   0.0449
  -1.500   0.3864   0.01646   0.01104  -0.1094   0.6816   0.0481
  -1.250   0.4123   0.01583   0.01026  -0.1092   0.6658   0.0509
  -1.000   0.4409   0.01695   0.01109  -0.1083   0.6503   0.0572
  -0.750   0.4654   0.01442   0.00846  -0.1086   0.6366   0.0628
   0.500   0.6017   0.01100   0.00396  -0.1057   0.5647   0.0454
   0.750   0.6278   0.01032   0.00321  -0.1052   0.5488   0.0431
   1.000   0.6539   0.01002   0.00281  -0.1047   0.5315   0.0422
   1.250   0.6799   0.00984   0.00254  -0.1041   0.5133   0.0421
   1.500   0.7060   0.00975   0.00237  -0.1037   0.4947   0.0428
   1.750   0.7320   0.00972   0.00226  -0.1032   0.4766   0.0436
   2.000   0.7580   0.00975   0.00221  -0.1027   0.4600   0.0443
   2.250   0.7840   0.00981   0.00218  -0.1023   0.4444   0.0461
   2.500   0.8101   0.00989   0.00218  -0.1019   0.4297   0.0487
   2.750   0.8362   0.00999   0.00224  -0.1015   0.4154   0.0525
   3.000   0.8617   0.00976   0.00245  -0.1012   0.4018   0.2918
   3.250   0.8935   0.00869   0.00267  -0.1024   0.3870   1.0000
   3.500   0.9194   0.00890   0.00279  -0.1020   0.3730   1.0000
   3.750   0.9451   0.00913   0.00294  -0.1015   0.3588   1.0000
   4.000   0.9708   0.00936   0.00310  -0.1011   0.3448   1.0000
   4.250   0.9963   0.00960   0.00328  -0.1007   0.3318   1.0000
   4.500   1.0216   0.00986   0.00347  -0.1002   0.3194   1.0000
   4.750   1.0468   0.01013   0.00367  -0.0997   0.3044   1.0000
   5.000   1.0718   0.01040   0.00388  -0.0992   0.2918   1.0000
   5.500   1.1219   0.01093   0.00432  -0.0983   0.2700   1.0000
   5.750   1.1470   0.01118   0.00457  -0.0978   0.2588   1.0000
   6.000   1.1718   0.01146   0.00482  -0.0973   0.2465   1.0000
   6.250   1.1959   0.01180   0.00509  -0.0968   0.2283   1.0000
   6.500   1.2151   0.01273   0.00554  -0.0956   0.1503   1.0000
   6.750   1.2225   0.01514   0.00725  -0.0928   0.0296   1.0000
   7.000   1.2449   0.01571   0.00794  -0.0918   0.0258   1.0000
   7.250   1.2665   0.01633   0.00865  -0.0908   0.0233   1.0000
   7.500   1.2855   0.01724   0.00964  -0.0894   0.0207   1.0000
   7.750   1.3026   0.01829   0.01083  -0.0877   0.0193   1.0000
   8.000   1.3219   0.01902   0.01165  -0.0864   0.0186   1.0000
   8.250   1.3394   0.01989   0.01262  -0.0848   0.0176   1.0000
   8.500   1.3551   0.02085   0.01366  -0.0831   0.0168   1.0000
   8.750   1.3699   0.02181   0.01470  -0.0812   0.0160   1.0000
   9.000   1.3814   0.02295   0.01589  -0.0790   0.0151   1.0000
   9.250   1.3821   0.02478   0.01781  -0.0753   0.0144   1.0000
   9.750   1.3822   0.02804   0.02126  -0.0676   0.0138   1.0000
  10.000   1.3907   0.02914   0.02245  -0.0652   0.0135   1.0000
  10.250   1.3963   0.03062   0.02402  -0.0628   0.0133   1.0000
  10.500   1.4020   0.03226   0.02575  -0.0605   0.0130   1.0000
  10.750   1.4084   0.03400   0.02757  -0.0585   0.0128   1.0000
  11.000   1.4159   0.03588   0.02955  -0.0567   0.0125   1.0000
  11.250   1.4244   0.03782   0.03159  -0.0550   0.0123   1.0000
  11.500   1.4328   0.03975   0.03361  -0.0536   0.0119   1.0000
  11.750   1.4400   0.04167   0.03564  -0.0522   0.0115   1.0000
  12.000   1.4462   0.04358   0.03762  -0.0511   0.0112   1.0000
  12.250   1.4515   0.04565   0.03976  -0.0501   0.0108   1.0000
  12.500   1.4598   0.04812   0.04235  -0.0490   0.0107   1.0000
  12.750   1.4666   0.05078   0.04512  -0.0480   0.0106   1.0000
  13.000   1.4722   0.05375   0.04825  -0.0470   0.0105   1.0000
  13.250   1.3366   0.05977   0.05512  -0.0431   0.0113   1.0000
  13.500   1.3273   0.06595   0.06157  -0.0430   0.0117   1.0000
  13.750   1.3116   0.07267   0.06855  -0.0435   0.0122   1.0000
  14.000   1.2928   0.07924   0.07534  -0.0447   0.0125   1.0000
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