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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.4 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe673-il-1000000.txt
Download as CSV file: xf-goe673-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3388   0.09516   0.09365  -0.0414   1.0000   0.0096
 -10.500  -0.4612   0.09802   0.09642  -0.0350   1.0000   0.0089
 -10.250  -0.4617   0.09368   0.09210  -0.0371   1.0000   0.0090
 -10.000  -0.4616   0.08944   0.08788  -0.0392   1.0000   0.0091
  -9.750  -0.4627   0.08495   0.08340  -0.0416   1.0000   0.0092
  -9.500  -0.4658   0.08007   0.07855  -0.0443   1.0000   0.0092
  -9.250  -0.4725   0.07481   0.07332  -0.0471   1.0000   0.0093
  -9.000  -0.5206   0.05580   0.05428  -0.0618   0.9980   0.0089
  -8.750  -0.5175   0.04680   0.04496  -0.0740   0.9920   0.0090
  -8.500  -0.5039   0.04196   0.03991  -0.0789   0.9879   0.0092
  -8.250  -0.4838   0.03872   0.03650  -0.0823   0.9852   0.0094
  -8.000  -0.4635   0.03586   0.03345  -0.0847   0.9817   0.0098
  -7.250  -0.4205   0.02092   0.01703  -0.0838   0.9613   0.0079
  -7.000  -0.4001   0.01805   0.01377  -0.0830   0.9561   0.0079
  -6.750  -0.3765   0.01678   0.01227  -0.0823   0.9500   0.0083
  -6.500  -0.3522   0.01572   0.01099  -0.0817   0.9446   0.0086
  -6.250  -0.3305   0.01339   0.00843  -0.0810   0.9391   0.0091
  -6.000  -0.3057   0.01250   0.00746  -0.0806   0.9332   0.0095
  -5.750  -0.2802   0.01185   0.00674  -0.0803   0.9282   0.0099
  -5.500  -0.2539   0.01131   0.00614  -0.0801   0.9222   0.0104
  -5.250  -0.2274   0.01089   0.00566  -0.0799   0.9165   0.0112
  -5.000  -0.2007   0.01039   0.00508  -0.0798   0.9108   0.0120
  -4.750  -0.1735   0.01003   0.00466  -0.0797   0.9045   0.0126
  -4.500  -0.1474   0.00922   0.00370  -0.0795   0.8987   0.0137
  -4.250  -0.1200   0.00877   0.00319  -0.0795   0.8919   0.0151
  -4.000  -0.0924   0.00852   0.00286  -0.0795   0.8858   0.0168
  -3.750  -0.0643   0.00832   0.00264  -0.0796   0.8786   0.0186
  -3.250  -0.0082   0.00772   0.00193  -0.0797   0.8648   0.0341
  -3.000   0.0183   0.00694   0.00162  -0.0799   0.8580   0.1706
  -2.750   0.0460   0.00652   0.00148  -0.0803   0.8501   0.2552
  -2.500   0.0739   0.00628   0.00138  -0.0805   0.8428   0.3124
  -2.250   0.1019   0.00601   0.00130  -0.0808   0.8344   0.3774
  -2.000   0.1298   0.00577   0.00125  -0.0810   0.8262   0.4489
  -1.750   0.1579   0.00561   0.00119  -0.0812   0.8173   0.5012
  -1.500   0.1862   0.00549   0.00115  -0.0814   0.8077   0.5372
  -1.250   0.2143   0.00536   0.00112  -0.0815   0.7979   0.5813
  -1.000   0.2423   0.00526   0.00110  -0.0817   0.7876   0.6308
  -0.750   0.2704   0.00520   0.00110  -0.0818   0.7760   0.6698
  -0.500   0.2986   0.00517   0.00110  -0.0819   0.7638   0.6983
  -0.250   0.3266   0.00516   0.00110  -0.0820   0.7508   0.7227
   0.000   0.3545   0.00515   0.00110  -0.0820   0.7368   0.7476
   0.250   0.3821   0.00514   0.00112  -0.0820   0.7219   0.7737
   0.500   0.4094   0.00514   0.00114  -0.0819   0.7063   0.8015
   0.750   0.4357   0.00511   0.00118  -0.0816   0.6901   0.8398
   1.000   0.4598   0.00507   0.00124  -0.0807   0.6730   0.8897
   1.250   0.4820   0.00508   0.00129  -0.0792   0.6562   0.9431
   1.500   0.5114   0.00513   0.00131  -0.0795   0.6403   0.9806
   1.750   0.5467   0.00521   0.00134  -0.0813   0.6255   1.0000
   2.000   0.5742   0.00532   0.00140  -0.0814   0.6121   1.0000
   2.250   0.6019   0.00543   0.00146  -0.0815   0.5993   1.0000
   2.500   0.6296   0.00555   0.00155  -0.0816   0.5859   1.0000
   2.750   0.6573   0.00567   0.00163  -0.0817   0.5729   1.0000
   3.000   0.6848   0.00581   0.00173  -0.0818   0.5576   1.0000
   3.250   0.7116   0.00601   0.00183  -0.0817   0.5328   1.0000
   3.500   0.7379   0.00625   0.00197  -0.0816   0.4997   1.0000
   3.750   0.7635   0.00657   0.00212  -0.0814   0.4604   1.0000
   4.000   0.7886   0.00694   0.00231  -0.0811   0.4164   1.0000
   4.250   0.8128   0.00742   0.00255  -0.0807   0.3621   1.0000
   4.500   0.8351   0.00809   0.00288  -0.0800   0.2887   1.0000
   4.750   0.8490   0.00970   0.00365  -0.0781   0.1242   1.0000
   5.000   0.8663   0.01098   0.00444  -0.0765   0.0220   1.0000
   5.250   0.8909   0.01143   0.00490  -0.0760   0.0162   1.0000
   5.500   0.9163   0.01176   0.00526  -0.0757   0.0147   1.0000
   5.750   0.9410   0.01216   0.00570  -0.0753   0.0132   1.0000
   6.000   0.9639   0.01275   0.00635  -0.0745   0.0117   1.0000
   6.250   0.9850   0.01351   0.00721  -0.0734   0.0107   1.0000
   6.500   1.0093   0.01387   0.00760  -0.0730   0.0100   1.0000
   6.750   1.0318   0.01441   0.00819  -0.0722   0.0093   1.0000
   7.000   1.0534   0.01501   0.00885  -0.0712   0.0088   1.0000
   7.250   1.0743   0.01564   0.00952  -0.0702   0.0083   1.0000
   7.500   1.0935   0.01640   0.01032  -0.0689   0.0078   1.0000
   7.750   1.1058   0.01777   0.01179  -0.0665   0.0074   1.0000
   8.000   1.1156   0.01957   0.01371  -0.0636   0.0070   1.0000
   8.250   1.1357   0.02021   0.01442  -0.0624   0.0068   1.0000
   8.500   1.1532   0.02123   0.01552  -0.0609   0.0066   1.0000
   8.750   1.1707   0.02229   0.01667  -0.0593   0.0063   1.0000
   9.000   1.1879   0.02333   0.01781  -0.0579   0.0060   1.0000
   9.250   1.2045   0.02441   0.01899  -0.0563   0.0057   1.0000
   9.500   1.2201   0.02592   0.02062  -0.0546   0.0056   1.0000
   9.750   1.2351   0.02756   0.02239  -0.0528   0.0055   1.0000
  10.000   1.2485   0.02922   0.02420  -0.0509   0.0053   1.0000
  10.250   1.2598   0.03094   0.02607  -0.0487   0.0052   1.0000
  10.500   1.2685   0.03288   0.02818  -0.0463   0.0052   1.0000
  10.750   1.2744   0.03451   0.02995  -0.0436   0.0050   1.0000
  11.000   1.2781   0.03628   0.03186  -0.0409   0.0050   1.0000
  11.250   1.2799   0.03800   0.03371  -0.0382   0.0049   1.0000
  11.500   1.2784   0.04026   0.03614  -0.0355   0.0048   1.0000
  11.750   1.2718   0.04321   0.03931  -0.0326   0.0047   1.0000
  12.000   1.2614   0.04666   0.04299  -0.0298   0.0047   1.0000
  12.250   1.2427   0.05109   0.04767  -0.0273   0.0046   1.0000
  12.500   1.2229   0.05579   0.05261  -0.0254   0.0046   1.0000
  12.750   1.2061   0.06030   0.05731  -0.0246   0.0046   1.0000
  13.000   1.1882   0.06528   0.06249  -0.0245   0.0046   1.0000
  13.250   1.1669   0.07107   0.06847  -0.0254   0.0046   1.0000
  13.500   1.1507   0.07662   0.07419  -0.0269   0.0046   1.0000
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