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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.51 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe673-il-1000000-n5.txt
Download as CSV file: xf-goe673-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4727   0.08520   0.08369  -0.0410   1.0000   0.0025
  -9.750  -0.4844   0.07828   0.07680  -0.0447   1.0000   0.0025
  -9.250  -0.5246   0.04712   0.04548  -0.0766   0.9803   0.0024
  -9.000  -0.5664   0.03010   0.02755  -0.0824   0.9599   0.0024
  -8.750  -0.5719   0.02207   0.01860  -0.0814   0.9473   0.0025
  -8.500  -0.5551   0.01957   0.01570  -0.0807   0.9389   0.0026
  -8.250  -0.5334   0.01819   0.01411  -0.0803   0.9313   0.0027
  -8.000  -0.5098   0.01726   0.01301  -0.0801   0.9255   0.0028
  -7.750  -0.4850   0.01650   0.01213  -0.0800   0.9194   0.0029
  -7.500  -0.4599   0.01588   0.01139  -0.0799   0.9136   0.0030
  -7.250  -0.4348   0.01503   0.01039  -0.0798   0.9080   0.0032
  -7.000  -0.4099   0.01404   0.00921  -0.0796   0.9020   0.0034
  -6.750  -0.3848   0.01306   0.00804  -0.0793   0.8965   0.0036
  -6.500  -0.3590   0.01227   0.00710  -0.0792   0.8905   0.0038
  -6.250  -0.3327   0.01167   0.00637  -0.0791   0.8847   0.0040
  -6.000  -0.3060   0.01107   0.00566  -0.0792   0.8787   0.0041
  -5.750  -0.2795   0.01043   0.00491  -0.0791   0.8723   0.0045
  -5.500  -0.2521   0.01008   0.00451  -0.0793   0.8662   0.0048
  -5.250  -0.2246   0.00976   0.00412  -0.0794   0.8594   0.0052
  -5.000  -0.1968   0.00947   0.00375  -0.0795   0.8530   0.0058
  -4.750  -0.1689   0.00925   0.00347  -0.0796   0.8456   0.0063
  -4.500  -0.1411   0.00887   0.00300  -0.0798   0.8382   0.0072
  -4.250  -0.1132   0.00864   0.00271  -0.0799   0.8302   0.0082
  -4.000  -0.0850   0.00844   0.00245  -0.0801   0.8217   0.0092
  -3.750  -0.0569   0.00831   0.00225  -0.0803   0.8130   0.0102
  -3.500  -0.0287   0.00810   0.00197  -0.0804   0.8035   0.0143
  -3.250  -0.0003   0.00795   0.00179  -0.0806   0.7941   0.0183
  -3.000   0.0275   0.00763   0.00157  -0.0809   0.7846   0.0618
  -2.750   0.0551   0.00724   0.00139  -0.0812   0.7739   0.1357
  -2.500   0.0833   0.00705   0.00127  -0.0814   0.7628   0.1724
  -2.250   0.1112   0.00677   0.00116  -0.0818   0.7510   0.2372
  -2.000   0.1389   0.00650   0.00109  -0.0821   0.7387   0.3144
  -1.750   0.1671   0.00641   0.00103  -0.0823   0.7253   0.3487
  -1.500   0.1953   0.00636   0.00098  -0.0825   0.7112   0.3751
  -1.250   0.2233   0.00629   0.00096  -0.0827   0.6962   0.4102
  -1.000   0.2514   0.00628   0.00094  -0.0830   0.6814   0.4371
  -0.750   0.2796   0.00627   0.00093  -0.0832   0.6666   0.4611
  -0.500   0.3077   0.00627   0.00093  -0.0834   0.6526   0.4838
  -0.250   0.3358   0.00628   0.00094  -0.0836   0.6391   0.5047
   0.000   0.3638   0.00627   0.00095  -0.0838   0.6257   0.5331
   0.250   0.3918   0.00624   0.00098  -0.0840   0.6130   0.5695
   0.500   0.4196   0.00619   0.00104  -0.0842   0.6001   0.6214
   0.750   0.4474   0.00619   0.00110  -0.0844   0.5870   0.6606
   1.000   0.4752   0.00622   0.00116  -0.0845   0.5721   0.6930
   1.250   0.5028   0.00626   0.00122  -0.0846   0.5564   0.7193
   1.500   0.5304   0.00631   0.00129  -0.0847   0.5415   0.7422
   1.750   0.5580   0.00635   0.00137  -0.0848   0.5286   0.7675
   2.000   0.5853   0.00637   0.00145  -0.0848   0.5160   0.7942
   2.250   0.6124   0.00639   0.00154  -0.0847   0.5038   0.8225
   2.500   0.6377   0.00638   0.00165  -0.0842   0.4906   0.8686
   2.750   0.6596   0.00636   0.00175  -0.0828   0.4783   0.9353
   3.000   0.6889   0.00640   0.00183  -0.0831   0.4665   0.9852
   3.250   0.7184   0.00656   0.00193  -0.0837   0.4490   1.0000
   3.500   0.7442   0.00687   0.00210  -0.0836   0.4145   1.0000
   3.750   0.7676   0.00743   0.00236  -0.0831   0.3470   1.0000
   4.000   0.7910   0.00801   0.00264  -0.0826   0.2848   1.0000
   4.250   0.8111   0.00894   0.00310  -0.0816   0.1900   1.0000
   4.500   0.8264   0.01042   0.00390  -0.0799   0.0414   1.0000
   4.750   0.8507   0.01088   0.00424  -0.0795   0.0164   1.0000
   5.000   0.8765   0.01117   0.00454  -0.0793   0.0111   1.0000
   5.250   0.9017   0.01153   0.00491  -0.0789   0.0081   1.0000
   5.500   0.9273   0.01182   0.00522  -0.0787   0.0073   1.0000
   5.750   0.9524   0.01214   0.00556  -0.0784   0.0063   1.0000
   6.000   0.9765   0.01257   0.00600  -0.0780   0.0052   1.0000
   6.250   1.0008   0.01296   0.00645  -0.0775   0.0048   1.0000
   6.500   1.0249   0.01335   0.00689  -0.0770   0.0044   1.0000
   6.750   1.0484   0.01379   0.00736  -0.0765   0.0040   1.0000
   7.000   1.0715   0.01424   0.00785  -0.0759   0.0037   1.0000
   7.250   1.0935   0.01478   0.00842  -0.0751   0.0034   1.0000
   7.500   1.1120   0.01562   0.00935  -0.0736   0.0031   1.0000
   7.750   1.1333   0.01616   0.00995  -0.0727   0.0030   1.0000
   8.000   1.1540   0.01672   0.01057  -0.0717   0.0028   1.0000
   8.250   1.1737   0.01733   0.01125  -0.0706   0.0026   1.0000
   8.500   1.1925   0.01800   0.01200  -0.0693   0.0024   1.0000
   8.750   1.2098   0.01873   0.01281  -0.0678   0.0023   1.0000
   9.000   1.2266   0.01946   0.01361  -0.0662   0.0022   1.0000
   9.250   1.2416   0.02021   0.01442  -0.0644   0.0021   1.0000
   9.500   1.2546   0.02096   0.01524  -0.0621   0.0021   1.0000
   9.750   1.2664   0.02184   0.01619  -0.0598   0.0020   1.0000
  10.000   1.2757   0.02294   0.01739  -0.0573   0.0019   1.0000
  10.250   1.2798   0.02454   0.01914  -0.0541   0.0018   1.0000
  10.500   1.2873   0.02596   0.02068  -0.0516   0.0018   1.0000
  10.750   1.2964   0.02725   0.02210  -0.0494   0.0017   1.0000
  11.000   1.3040   0.02872   0.02372  -0.0472   0.0017   1.0000
  11.250   1.3114   0.03025   0.02538  -0.0451   0.0017   1.0000
  11.500   1.3161   0.03212   0.02741  -0.0429   0.0016   1.0000
  11.750   1.3195   0.03415   0.02965  -0.0407   0.0016   1.0000
  12.000   1.3208   0.03650   0.03219  -0.0385   0.0015   1.0000
  12.250   1.3190   0.03922   0.03513  -0.0362   0.0015   1.0000
  12.500   1.3136   0.04244   0.03859  -0.0341   0.0014   1.0000
  12.750   1.3030   0.04637   0.04278  -0.0320   0.0014   1.0000
  13.000   1.2863   0.05122   0.04793  -0.0302   0.0013   1.0000
  13.250   1.2567   0.05811   0.05518  -0.0288   0.0013   1.0000
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