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GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 426 AIRFOIL (goe426-il)
Reynolds number: 100,000
Max Cl/Cd: 46.87 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe426-il-100000.txt
Download as CSV file: xf-goe426-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 426 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2823   0.10270   0.09823  -0.0379   1.0000   0.1157
  -8.500  -0.3108   0.10317   0.09886  -0.0339   1.0000   0.1169
  -8.250  -0.3456   0.10268   0.09852  -0.0439   0.9893   0.1192
  -8.000  -0.3026   0.09619   0.09198  -0.0421   0.9883   0.1221
  -7.750  -0.2677   0.09214   0.08789  -0.0456   0.9830   0.1276
  -7.500  -0.2808   0.08599   0.08173  -0.0702   0.9587   0.1361
  -7.250  -0.2344   0.08315   0.07890  -0.0605   0.9604   0.1396
  -7.000  -0.2288   0.07641   0.07203  -0.0832   0.9418   0.1526
  -6.750  -0.1811   0.07428   0.06998  -0.0741   0.9421   0.1575
  -6.500  -0.1678   0.06866   0.06427  -0.0869   0.9272   0.1707
  -6.250  -0.1351   0.06637   0.06199  -0.0853   0.9193   0.1773
  -6.000  -0.1118   0.06195   0.05750  -0.0921   0.9095   0.1907
  -5.750  -0.0988   0.05860   0.05407  -0.0959   0.8950   0.2054
  -5.250  -0.0654   0.05356   0.04891  -0.0982   0.8697   0.2381
  -5.000  -0.0419   0.05143   0.04674  -0.0977   0.8606   0.2563
  -4.750  -0.0264   0.05004   0.04535  -0.0957   0.8476   0.2770
  -4.250   0.0318   0.03226   0.02486  -0.1130   0.8269   0.1138
  -4.000   0.0569   0.03077   0.02259  -0.1119   0.8148   0.1035
  -3.750   0.0826   0.02869   0.02031  -0.1116   0.8054   0.1015
  -3.500   0.1107   0.02712   0.01845  -0.1113   0.7967   0.1001
  -3.250   0.1360   0.02618   0.01725  -0.1106   0.7868   0.1009
  -3.000   0.1657   0.02518   0.01596  -0.1103   0.7795   0.1023
  -2.750   0.1906   0.02443   0.01506  -0.1096   0.7695   0.1028
  -2.500   0.2204   0.02356   0.01399  -0.1093   0.7628   0.1036
  -2.250   0.2443   0.02283   0.01327  -0.1085   0.7534   0.1053
  -2.000   0.2721   0.02201   0.01249  -0.1081   0.7468   0.1090
  -1.750   0.2956   0.02174   0.01225  -0.1073   0.7382   0.1153
  -1.500   0.3219   0.02122   0.01173  -0.1067   0.7313   0.1223
  -1.250   0.3462   0.02093   0.01146  -0.1060   0.7242   0.1325
  -1.000   0.3707   0.02054   0.01113  -0.1053   0.7167   0.1541
  -0.750   0.3851   0.01847   0.01117  -0.1021   0.7120   0.6748
  -0.500   0.3951   0.01852   0.01163  -0.0974   0.7037   0.8145
  -0.250   0.4692   0.01803   0.01114  -0.1041   0.6976   0.9950
   0.000   0.4897   0.01839   0.01129  -0.1037   0.6906   1.0000
   0.250   0.5116   0.01872   0.01144  -0.1031   0.6835   1.0000
   0.500   0.5403   0.01885   0.01132  -0.1031   0.6786   1.0000
   0.750   0.5598   0.01943   0.01183  -0.1024   0.6704   1.0000
   1.000   0.5869   0.01965   0.01188  -0.1022   0.6646   1.0000
   1.250   0.6118   0.02004   0.01214  -0.1019   0.6586   1.0000
   1.500   0.6348   0.02050   0.01253  -0.1014   0.6514   1.0000
   1.750   0.6640   0.02065   0.01252  -0.1014   0.6466   1.0000
   2.000   0.6846   0.02130   0.01315  -0.1007   0.6392   1.0000
   2.250   0.7106   0.02162   0.01339  -0.1004   0.6332   1.0000
   2.500   0.7415   0.02172   0.01335  -0.1006   0.6290   1.0000
   2.750   0.7583   0.02258   0.01426  -0.0995   0.6206   1.0000
   3.000   0.7867   0.02277   0.01436  -0.0994   0.6154   1.0000
   3.250   0.8101   0.02332   0.01490  -0.0989   0.6095   1.0000
   3.500   0.8321   0.02391   0.01549  -0.0982   0.6025   1.0000
   3.750   0.8629   0.02398   0.01546  -0.0984   0.5979   1.0000
   4.000   0.8793   0.02495   0.01651  -0.0972   0.5902   1.0000
   4.250   0.9058   0.02530   0.01684  -0.0970   0.5845   1.0000
   4.500   0.9386   0.02532   0.01676  -0.0973   0.5806   1.0000
   4.750   0.9491   0.02662   0.01822  -0.0955   0.5716   1.0000
   5.000   0.9793   0.02675   0.01831  -0.0956   0.5668   1.0000
   5.250   0.9983   0.02767   0.01929  -0.0947   0.5606   1.0000
   5.500   1.0174   0.02849   0.02017  -0.0938   0.5536   1.0000
   5.750   1.0508   0.02846   0.02011  -0.0942   0.5494   1.0000
   6.000   1.0578   0.03010   0.02191  -0.0921   0.5411   1.0000
   6.250   1.0836   0.03056   0.02240  -0.0918   0.5359   1.0000
   6.500   1.1193   0.03047   0.02228  -0.0925   0.5323   1.0000
   6.750   1.1142   0.03285   0.02488  -0.0893   0.5227   1.0000
   7.000   1.1467   0.03287   0.02492  -0.0896   0.5184   1.0000
   7.250   1.1756   0.03330   0.02538  -0.0897   0.5143   1.0000
   7.500   1.1618   0.03625   0.02854  -0.0858   0.5046   1.0000
   7.750   1.2022   0.03577   0.02809  -0.0868   0.5012   1.0000
   8.000   1.1676   0.04025   0.03277  -0.0813   0.4908   1.0000
   8.250   1.1983   0.04036   0.03296  -0.0814   0.4866   1.0000
   8.500   1.2512   0.03906   0.03171  -0.0833   0.4840   1.0000
   8.750   1.0845   0.05389   0.04660  -0.0707   0.4641   1.0000
   9.000   1.1587   0.04970   0.04254  -0.0717   0.4643   1.0000
   9.250   1.0846   0.05988   0.05270  -0.0690   0.4499   1.0000
   9.500   1.1629   0.05375   0.04675  -0.0683   0.4492   1.0000
   9.750   0.9834   0.07749   0.07031  -0.0689   0.4228   1.0000
  10.000   1.0582   0.07124   0.06421  -0.0669   0.4206   1.0000
  10.250   1.1376   0.06390   0.05707  -0.0647   0.4201   1.0000
  10.500   1.2220   0.05639   0.04979  -0.0633   0.4208   1.0000
  10.750   1.2807   0.05265   0.04623  -0.0629   0.4176   1.0000
  11.000   1.4932   0.03259   0.02594  -0.0706   0.3848   1.0000
  11.250   1.5065   0.03214   0.02551  -0.0679   0.3725   1.0000
  11.500   1.4993   0.03298   0.02650  -0.0634   0.3614   1.0000
  11.750   1.4940   0.03391   0.02754  -0.0596   0.3492   1.0000
  12.000   1.4892   0.03498   0.02870  -0.0563   0.3356   1.0000
  12.250   1.4807   0.03654   0.03034  -0.0532   0.3206   1.0000
  12.500   1.4689   0.03869   0.03256  -0.0505   0.3038   1.0000
  12.750   1.4546   0.04138   0.03525  -0.0483   0.2839   1.0000
  13.000   1.4336   0.04529   0.03924  -0.0468   0.2631   1.0000
  13.250   1.4107   0.04978   0.04367  -0.0459   0.2368   1.0000
  13.500   1.3844   0.05510   0.04886  -0.0455   0.2051   1.0000
  13.750   1.3558   0.06107   0.05458  -0.0456   0.1740   1.0000
  14.000   1.3279   0.06739   0.06065  -0.0462   0.1501   1.0000
  14.250   1.3006   0.07398   0.06700  -0.0470   0.1303   1.0000
  14.500   1.2772   0.08024   0.07302  -0.0479   0.1141   1.0000
  14.750   1.2617   0.08558   0.07820  -0.0485   0.0989   1.0000
  15.000   1.2555   0.08952   0.08200  -0.0486   0.0870   1.0000
  15.250   1.2570   0.09223   0.08457  -0.0482   0.0783   1.0000
  15.500   1.2638   0.09444   0.08681  -0.0478   0.0716   1.0000
  15.750   1.2779   0.09517   0.08739  -0.0465   0.0660   1.0000
  16.000   1.2928   0.09617   0.08844  -0.0453   0.0620   1.0000
  16.250   1.3272   0.09409   0.08608  -0.0419   0.0577   1.0000
  16.500   1.3353   0.09654   0.08877  -0.0418   0.0558   1.0000
  16.750   1.3444   0.09886   0.09126  -0.0416   0.0536   1.0000
  17.000   1.3562   0.10079   0.09325  -0.0412   0.0516   1.0000
  17.250   1.3854   0.10079   0.09320  -0.0392   0.0497   1.0000
  17.500   1.3970   0.10358   0.09617  -0.0388   0.0489   1.0000
  17.750   1.3921   0.10805   0.10093  -0.0400   0.0486   1.0000
  18.000   1.3839   0.11301   0.10618  -0.0416   0.0483   1.0000
  18.250   1.3723   0.11851   0.11196  -0.0438   0.0481   1.0000
  18.500   1.3579   0.12457   0.11829  -0.0466   0.0480   1.0000
  18.750   1.3416   0.13112   0.12510  -0.0500   0.0480   1.0000
  19.000   1.3229   0.13833   0.13256  -0.0539   0.0481   1.0000
  19.250   1.3023   0.14618   0.14064  -0.0586   0.0483   1.0000
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