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GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 549 AIRFOIL (goe549-il)
Reynolds number: 500,000
Max Cl/Cd: 100.8 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe549-il-500000-n5.txt
Download as CSV file: xf-goe549-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 549 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5324   0.03131   0.02769  -0.1159   0.8868   0.0144
 -10.750  -0.5420   0.02797   0.02391  -0.1142   0.8690   0.0145
 -10.500  -0.5302   0.02677   0.02254  -0.1130   0.8561   0.0147
 -10.250  -0.5125   0.02614   0.02181  -0.1122   0.8451   0.0148
 -10.000  -0.4969   0.02514   0.02063  -0.1111   0.8345   0.0150
  -9.750  -0.4782   0.02449   0.01986  -0.1103   0.8231   0.0151
  -9.500  -0.4591   0.02380   0.01903  -0.1094   0.8111   0.0154
  -9.250  -0.4403   0.02298   0.01805  -0.1085   0.7992   0.0156
  -9.000  -0.4217   0.02202   0.01689  -0.1076   0.7862   0.0159
  -8.750  -0.4027   0.02106   0.01571  -0.1066   0.7718   0.0164
  -8.500  -0.3840   0.01989   0.01427  -0.1055   0.7548   0.0171
  -8.250  -0.3649   0.01872   0.01276  -0.1043   0.7343   0.0179
  -8.000  -0.3438   0.01811   0.01194  -0.1033   0.7108   0.0184
  -7.750  -0.3209   0.01781   0.01151  -0.1026   0.6898   0.0187
  -7.500  -0.2974   0.01757   0.01115  -0.1019   0.6732   0.0191
  -7.250  -0.2736   0.01727   0.01071  -0.1013   0.6606   0.0196
  -6.750  -0.2252   0.01647   0.00964  -0.1002   0.6427   0.0210
  -6.500  -0.2005   0.01608   0.00909  -0.0997   0.6358   0.0217
  -6.250  -0.1752   0.01575   0.00863  -0.0992   0.6299   0.0223
  -6.000  -0.1501   0.01532   0.00808  -0.0988   0.6242   0.0228
  -5.750  -0.1259   0.01478   0.00749  -0.0983   0.6193   0.0235
  -5.500  -0.1002   0.01448   0.00715  -0.0979   0.6149   0.0242
  -5.250  -0.0741   0.01422   0.00685  -0.0976   0.6104   0.0250
  -5.000  -0.0480   0.01400   0.00657  -0.0973   0.6060   0.0260
  -4.750  -0.0219   0.01380   0.00629  -0.0970   0.6020   0.0270
  -4.500   0.0047   0.01358   0.00601  -0.0967   0.5983   0.0277
  -4.250   0.0311   0.01332   0.00569  -0.0964   0.5943   0.0281
  -4.000   0.0574   0.01305   0.00536  -0.0961   0.5904   0.0283
  -3.750   0.0821   0.01255   0.00481  -0.0955   0.5868   0.0288
  -3.500   0.1077   0.01217   0.00440  -0.0951   0.5833   0.0293
  -3.250   0.1338   0.01187   0.00407  -0.0948   0.5794   0.0298
  -3.000   0.1601   0.01163   0.00381  -0.0945   0.5753   0.0303
  -2.750   0.1864   0.01146   0.00359  -0.0941   0.5712   0.0311
  -2.500   0.2131   0.01128   0.00338  -0.0939   0.5672   0.0318
  -2.250   0.2400   0.01111   0.00319  -0.0936   0.5627   0.0324
  -2.000   0.2668   0.01098   0.00302  -0.0934   0.5584   0.0331
  -1.750   0.2936   0.01088   0.00287  -0.0931   0.5546   0.0337
  -1.500   0.3208   0.01077   0.00274  -0.0929   0.5507   0.0344
  -1.250   0.3481   0.01069   0.00263  -0.0928   0.5465   0.0351
  -1.000   0.3752   0.01062   0.00252  -0.0925   0.5423   0.0361
  -0.750   0.4020   0.01056   0.00242  -0.0923   0.5385   0.0385
  -0.500   0.4293   0.01047   0.00236  -0.0921   0.5343   0.0419
  -0.250   0.4555   0.01023   0.00230  -0.0919   0.5297   0.0961
   0.000   0.4804   0.00986   0.00225  -0.0915   0.5254   0.2053
   0.250   0.5056   0.00960   0.00225  -0.0911   0.5213   0.3056
   0.750   0.5565   0.00918   0.00231  -0.0904   0.5112   0.4694
   1.000   0.5814   0.00906   0.00237  -0.0898   0.5068   0.5458
   1.250   0.6074   0.00898   0.00242  -0.0894   0.5017   0.5933
   1.500   0.6320   0.00887   0.00248  -0.0888   0.4959   0.6535
   1.750   0.6547   0.00871   0.00254  -0.0876   0.4906   0.7307
   2.250   0.7606   0.00845   0.00275  -0.0984   0.4765   0.9992
   2.500   0.7865   0.00854   0.00281  -0.0980   0.4699   1.0000
   2.750   0.8105   0.00867   0.00287  -0.0972   0.4631   1.0000
   3.000   0.8353   0.00877   0.00295  -0.0966   0.4570   1.0000
   3.250   0.8596   0.00890   0.00303  -0.0959   0.4500   1.0000
   3.500   0.8838   0.00903   0.00312  -0.0952   0.4429   1.0000
   3.750   0.9076   0.00919   0.00323  -0.0945   0.4338   1.0000
   4.000   0.9308   0.00937   0.00334  -0.0936   0.4212   1.0000
   4.250   0.9543   0.00954   0.00347  -0.0929   0.4120   1.0000
   4.500   0.9769   0.00976   0.00362  -0.0919   0.3994   1.0000
   4.750   1.0001   0.00997   0.00378  -0.0911   0.3888   1.0000
   5.000   1.0235   0.01016   0.00394  -0.0903   0.3802   1.0000
   5.250   1.0463   0.01038   0.00412  -0.0895   0.3720   1.0000
   5.500   1.0688   0.01062   0.00431  -0.0886   0.3604   1.0000
   5.750   1.0904   0.01089   0.00453  -0.0875   0.3484   1.0000
   6.000   1.1121   0.01116   0.00475  -0.0865   0.3394   1.0000
   6.250   1.1345   0.01139   0.00497  -0.0856   0.3309   1.0000
   6.500   1.1555   0.01167   0.00522  -0.0845   0.3211   1.0000
   6.750   1.1764   0.01196   0.00548  -0.0834   0.3122   1.0000
   7.000   1.1970   0.01225   0.00574  -0.0822   0.3021   1.0000
   7.250   1.2167   0.01257   0.00604  -0.0809   0.2937   1.0000
   7.500   1.2378   0.01281   0.00630  -0.0799   0.2878   1.0000
   7.750   1.2566   0.01314   0.00660  -0.0784   0.2806   1.0000
   8.000   1.2752   0.01341   0.00689  -0.0769   0.2735   1.0000
   8.250   1.2903   0.01379   0.00724  -0.0748   0.2641   1.0000
   8.500   1.3072   0.01411   0.00758  -0.0731   0.2565   1.0000
   8.750   1.3217   0.01453   0.00798  -0.0710   0.2469   1.0000
   9.000   1.3346   0.01504   0.00845  -0.0687   0.2343   1.0000
   9.250   1.3475   0.01557   0.00896  -0.0666   0.2227   1.0000
   9.500   1.3601   0.01614   0.00951  -0.0644   0.2108   1.0000
   9.750   1.3726   0.01674   0.01010  -0.0624   0.2006   1.0000
  10.000   1.3811   0.01756   0.01087  -0.0600   0.1851   1.0000
  10.250   1.3856   0.01865   0.01187  -0.0572   0.1661   1.0000
  10.500   1.3838   0.02017   0.01327  -0.0541   0.1386   1.0000
  10.750   1.3684   0.02269   0.01555  -0.0499   0.0976   1.0000
  11.000   1.3687   0.02440   0.01721  -0.0477   0.0845   1.0000
  11.250   1.3732   0.02593   0.01875  -0.0460   0.0776   1.0000
  11.500   1.3816   0.02723   0.02011  -0.0448   0.0728   1.0000
  11.750   1.3878   0.02877   0.02168  -0.0435   0.0679   1.0000
  12.000   1.3933   0.03044   0.02338  -0.0424   0.0629   1.0000
  12.250   1.3950   0.03249   0.02544  -0.0412   0.0539   1.0000
  12.500   1.3923   0.03505   0.02797  -0.0401   0.0417   1.0000
  12.750   1.3865   0.03803   0.03092  -0.0391   0.0309   1.0000
  13.000   1.3850   0.04070   0.03362  -0.0384   0.0263   1.0000
  13.250   1.3851   0.04329   0.03626  -0.0379   0.0237   1.0000
  13.500   1.3860   0.04584   0.03887  -0.0375   0.0220   1.0000
  13.750   1.3865   0.04847   0.04156  -0.0371   0.0209   1.0000
  14.000   1.3871   0.05114   0.04431  -0.0369   0.0199   1.0000
  14.250   1.3881   0.05380   0.04705  -0.0367   0.0190   1.0000
  14.500   1.3875   0.05667   0.05001  -0.0365   0.0181   1.0000
  14.750   1.3863   0.05970   0.05310  -0.0365   0.0173   1.0000
  15.000   1.3847   0.06283   0.05632  -0.0365   0.0168   1.0000
  15.250   1.3827   0.06605   0.05963  -0.0367   0.0165   1.0000
  15.500   1.3800   0.06945   0.06310  -0.0369   0.0158   1.0000
  15.750   1.3798   0.07257   0.06631  -0.0372   0.0154   1.0000
  16.000   1.3786   0.07589   0.06972  -0.0376   0.0152   1.0000
  16.250   1.3764   0.07936   0.07329  -0.0381   0.0148   1.0000
  16.500   1.3743   0.08288   0.07690  -0.0386   0.0143   1.0000
  16.750   1.3714   0.08658   0.08067  -0.0393   0.0139   1.0000
  17.000   1.3683   0.09033   0.08452  -0.0400   0.0137   1.0000
  17.250   1.3642   0.09429   0.08856  -0.0409   0.0132   1.0000
  17.500   1.3590   0.09844   0.09278  -0.0419   0.0128   1.0000
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