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GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 723 AIRFOIL (goe723-il)
Reynolds number: 500,000
Max Cl/Cd: 103.47 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe723-il-500000-n5.txt
Download as CSV file: xf-goe723-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 723 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3471   0.10115   0.09864  -0.0414   1.0000   0.0216
 -10.250  -0.3497   0.09713   0.09463  -0.0425   1.0000   0.0217
  -9.750  -0.5089   0.03963   0.03652  -0.0981   0.9540   0.0232
  -9.500  -0.4864   0.03420   0.03072  -0.1069   0.9388   0.0233
  -9.250  -0.4505   0.03105   0.02731  -0.1134   0.9275   0.0236
  -9.000  -0.4124   0.02898   0.02503  -0.1186   0.9135   0.0239
  -8.750  -0.3806   0.02737   0.02320  -0.1215   0.8955   0.0242
  -8.500  -0.3579   0.02578   0.02135  -0.1224   0.8760   0.0244
  -8.250  -0.3385   0.02431   0.01962  -0.1222   0.8577   0.0247
  -8.000  -0.3199   0.02288   0.01791  -0.1216   0.8413   0.0248
  -7.750  -0.3004   0.02166   0.01644  -0.1208   0.8263   0.0250
  -7.500  -0.2802   0.02058   0.01512  -0.1200   0.8120   0.0253
  -7.000  -0.2376   0.01864   0.01274  -0.1183   0.7863   0.0257
  -6.750  -0.2152   0.01780   0.01171  -0.1175   0.7754   0.0259
  -6.250  -0.1688   0.01641   0.00998  -0.1160   0.7545   0.0264
  -6.000  -0.1447   0.01589   0.00929  -0.1153   0.7455   0.0268
  -5.750  -0.1201   0.01541   0.00868  -0.1147   0.7369   0.0271
  -5.500  -0.0956   0.01490   0.00805  -0.1140   0.7290   0.0272
  -5.250  -0.0707   0.01444   0.00749  -0.1134   0.7208   0.0274
  -5.000  -0.0457   0.01406   0.00700  -0.1128   0.7133   0.0275
  -4.750  -0.0216   0.01336   0.00624  -0.1121   0.7061   0.0278
  -4.500   0.0030   0.01288   0.00570  -0.1114   0.6994   0.0281
  -4.250   0.0281   0.01249   0.00528  -0.1109   0.6930   0.0285
  -4.000   0.0534   0.01215   0.00490  -0.1103   0.6861   0.0287
  -3.750   0.0787   0.01187   0.00456  -0.1097   0.6797   0.0290
  -3.500   0.1045   0.01159   0.00426  -0.1092   0.6734   0.0294
  -3.250   0.1302   0.01135   0.00398  -0.1087   0.6673   0.0298
  -3.000   0.1560   0.01113   0.00372  -0.1082   0.6615   0.0301
  -2.750   0.1822   0.01092   0.00348  -0.1077   0.6552   0.0306
  -2.500   0.2082   0.01075   0.00327  -0.1072   0.6490   0.0313
  -2.250   0.2345   0.01059   0.00307  -0.1067   0.6436   0.0319
  -2.000   0.2609   0.01044   0.00289  -0.1063   0.6374   0.0324
  -1.750   0.2871   0.01032   0.00272  -0.1058   0.6314   0.0328
  -1.500   0.3134   0.01014   0.00252  -0.1054   0.6255   0.0334
  -1.250   0.3396   0.01001   0.00235  -0.1049   0.6179   0.0343
  -1.000   0.3657   0.00993   0.00223  -0.1044   0.6097   0.0353
  -0.750   0.3920   0.00986   0.00213  -0.1039   0.6010   0.0364
  -0.500   0.4184   0.00982   0.00205  -0.1034   0.5945   0.0376
  -0.250   0.4452   0.00977   0.00198  -0.1031   0.5881   0.0392
   0.000   0.4714   0.00972   0.00192  -0.1026   0.5821   0.0444
   0.250   0.4959   0.00926   0.00185  -0.1020   0.5765   0.1697
   0.500   0.5212   0.00903   0.00187  -0.1015   0.5701   0.2528
   0.750   0.5468   0.00895   0.00191  -0.1010   0.5644   0.3093
   1.000   0.5732   0.00889   0.00196  -0.1006   0.5588   0.3487
   1.250   0.5994   0.00887   0.00202  -0.1001   0.5526   0.3808
   1.500   0.6251   0.00888   0.00207  -0.0996   0.5456   0.4105
   1.750   0.6507   0.00885   0.00214  -0.0990   0.5365   0.4471
   2.000   0.6758   0.00886   0.00221  -0.0984   0.5270   0.4806
   2.250   0.7004   0.00887   0.00230  -0.0976   0.5163   0.5192
   2.500   0.7256   0.00885   0.00239  -0.0969   0.5085   0.5639
   2.750   0.7497   0.00887   0.00247  -0.0961   0.4989   0.6021
   3.000   0.7729   0.00880   0.00257  -0.0950   0.4873   0.6621
   3.500   0.8875   0.00862   0.00291  -0.1082   0.4545   1.0000
   3.750   0.9116   0.00881   0.00303  -0.1074   0.4396   1.0000
   4.000   0.9342   0.00907   0.00318  -0.1063   0.4179   1.0000
   4.250   0.9563   0.00937   0.00336  -0.1051   0.3918   1.0000
   4.500   0.9780   0.00969   0.00356  -0.1039   0.3693   1.0000
   4.750   1.0001   0.01001   0.00378  -0.1028   0.3490   1.0000
   5.000   1.0211   0.01038   0.00403  -0.1015   0.3267   1.0000
   5.250   1.0421   0.01075   0.00430  -0.1001   0.3062   1.0000
   5.500   1.0631   0.01112   0.00458  -0.0988   0.2853   1.0000
   5.750   1.0819   0.01160   0.00492  -0.0972   0.2560   1.0000
   6.000   1.0952   0.01242   0.00542  -0.0947   0.2000   1.0000
   6.250   1.0978   0.01385   0.00635  -0.0905   0.1115   1.0000
   6.500   1.1156   0.01435   0.00678  -0.0887   0.0955   1.0000
   7.000   1.1491   0.01540   0.00767  -0.0848   0.0659   1.0000
   7.250   1.1672   0.01581   0.00807  -0.0831   0.0616   1.0000
   7.500   1.1839   0.01622   0.00848  -0.0812   0.0591   1.0000
   7.750   1.1989   0.01665   0.00893  -0.0789   0.0568   1.0000
   8.000   1.2130   0.01714   0.00942  -0.0765   0.0546   1.0000
   8.250   1.2280   0.01760   0.00991  -0.0744   0.0532   1.0000
   8.500   1.2437   0.01805   0.01040  -0.0724   0.0523   1.0000
   8.750   1.2590   0.01854   0.01095  -0.0704   0.0514   1.0000
   9.000   1.2737   0.01908   0.01153  -0.0685   0.0505   1.0000
   9.250   1.2877   0.01967   0.01217  -0.0665   0.0493   1.0000
   9.500   1.3007   0.02035   0.01287  -0.0645   0.0479   1.0000
   9.750   1.3122   0.02114   0.01369  -0.0625   0.0465   1.0000
  10.000   1.3205   0.02217   0.01475  -0.0602   0.0447   1.0000
  10.250   1.3350   0.02286   0.01550  -0.0587   0.0440   1.0000
  10.500   1.3486   0.02363   0.01634  -0.0572   0.0431   1.0000
  10.750   1.3608   0.02454   0.01731  -0.0557   0.0422   1.0000
  11.000   1.3732   0.02548   0.01830  -0.0544   0.0410   1.0000
  11.250   1.3844   0.02652   0.01939  -0.0530   0.0399   1.0000
  11.500   1.3944   0.02772   0.02062  -0.0517   0.0389   1.0000
  11.750   1.4020   0.02914   0.02209  -0.0503   0.0380   1.0000
  12.000   1.4108   0.03053   0.02354  -0.0490   0.0371   1.0000
  12.250   1.4219   0.03176   0.02485  -0.0481   0.0363   1.0000
  12.500   1.4315   0.03313   0.02630  -0.0471   0.0353   1.0000
  12.750   1.4412   0.03454   0.02777  -0.0462   0.0342   1.0000
  13.000   1.4499   0.03607   0.02935  -0.0453   0.0333   1.0000
  13.250   1.4576   0.03771   0.03102  -0.0445   0.0321   1.0000
  13.500   1.4628   0.03962   0.03299  -0.0437   0.0313   1.0000
  13.750   1.4710   0.04127   0.03473  -0.0430   0.0302   1.0000
  14.000   1.4784   0.04303   0.03656  -0.0423   0.0289   1.0000
  14.250   1.4843   0.04496   0.03854  -0.0417   0.0278   1.0000
  14.500   1.4891   0.04704   0.04066  -0.0411   0.0268   1.0000
  14.750   1.4933   0.04923   0.04293  -0.0406   0.0259   1.0000
  15.000   1.4976   0.05145   0.04524  -0.0402   0.0247   1.0000
  15.250   1.5012   0.05377   0.04762  -0.0399   0.0235   1.0000
  15.500   1.5038   0.05626   0.05015  -0.0396   0.0225   1.0000
  15.750   1.5058   0.05887   0.05283  -0.0394   0.0214   1.0000
  16.000   1.5074   0.06156   0.05560  -0.0392   0.0204   1.0000
  16.250   1.5080   0.06441   0.05852  -0.0392   0.0195   1.0000
  16.500   1.5077   0.06742   0.06160  -0.0393   0.0188   1.0000
  16.750   1.5067   0.07057   0.06482  -0.0394   0.0182   1.0000
  17.000   1.5062   0.07369   0.06803  -0.0396   0.0175   1.0000
  17.250   1.5045   0.07703   0.07146  -0.0399   0.0169   1.0000
  17.500   1.5021   0.08047   0.07498  -0.0403   0.0164   1.0000
  17.750   1.4993   0.08403   0.07862  -0.0408   0.0159   1.0000
  18.000   1.4954   0.08780   0.08246  -0.0414   0.0154   1.0000
  18.250   1.4907   0.09173   0.08647  -0.0422   0.0150   1.0000
  18.500   1.4872   0.09550   0.09034  -0.0430   0.0147   1.0000
  18.750   1.4834   0.09937   0.09431  -0.0438   0.0143   1.0000
  19.000   1.4794   0.10329   0.09833  -0.0448   0.0140   1.0000
  19.250   1.4743   0.10746   0.10260  -0.0460   0.0137   1.0000
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