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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 100,000
Max Cl/Cd: 51.81 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe385-il-100000.txt
Download as CSV file: xf-goe385-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2830   0.10851   0.10394  -0.0296   1.0000   0.0666
  -9.500  -0.2920   0.10661   0.10212  -0.0326   1.0000   0.0671
  -9.250  -0.3000   0.10434   0.09991  -0.0353   1.0000   0.0673
  -9.000  -0.2661   0.09599   0.09153  -0.0298   1.0000   0.0707
  -8.750  -0.2608   0.09262   0.08818  -0.0298   1.0000   0.0732
  -8.500  -0.2593   0.08940   0.08501  -0.0304   1.0000   0.0758
  -8.250  -0.2612   0.08636   0.08202  -0.0314   1.0000   0.0783
  -7.500  -0.3479   0.08772   0.08325  -0.0286   1.0000   0.0763
  -7.250  -0.3493   0.08485   0.08046  -0.0316   1.0000   0.0789
  -7.000  -0.3562   0.08275   0.07840  -0.0380   1.0000   0.0812
  -6.750  -0.3646   0.08166   0.07715  -0.0421   1.0000   0.0820
  -6.500  -0.3626   0.07612   0.07185  -0.0375   1.0000   0.0834
  -6.250  -0.3630   0.07365   0.06949  -0.0332   1.0000   0.0853
  -6.000  -0.3662   0.07171   0.06761  -0.0307   1.0000   0.0878
  -5.750  -0.3696   0.06976   0.06567  -0.0296   1.0000   0.0912
  -5.500  -0.3676   0.06892   0.06436  -0.0360   1.0000   0.0974
  -5.250  -0.3505   0.06338   0.05918  -0.0344   0.9959   0.1015
  -5.000  -0.3061   0.05838   0.05388  -0.0441   0.9872   0.1146
  -4.750  -0.2650   0.05432   0.04956  -0.0510   0.9787   0.1293
  -4.500  -0.2258   0.05030   0.04541  -0.0562   0.9716   0.1453
  -4.250  -0.1929   0.04706   0.04218  -0.0593   0.9622   0.1647
  -4.000  -0.1538   0.04390   0.03891  -0.0638   0.9549   0.1954
  -3.750  -0.1187   0.04126   0.03615  -0.0673   0.9456   0.2378
  -2.750   0.0781   0.02832   0.02082  -0.0843   0.9143   0.1456
  -2.500   0.1164   0.02617   0.01816  -0.0849   0.9037   0.1188
  -2.250   0.1555   0.02491   0.01639  -0.0858   0.8948   0.1105
  -2.000   0.1918   0.02322   0.01448  -0.0866   0.8859   0.1052
  -1.750   0.2238   0.02211   0.01310  -0.0864   0.8742   0.1014
  -1.500   0.2550   0.02116   0.01198  -0.0859   0.8625   0.0999
  -1.250   0.2848   0.02024   0.01102  -0.0854   0.8514   0.1023
  -1.000   0.3133   0.01949   0.01024  -0.0846   0.8406   0.1061
  -0.750   0.3391   0.01896   0.00970  -0.0836   0.8282   0.1079
  -0.500   0.3647   0.01855   0.00926  -0.0826   0.8165   0.1106
  -0.250   0.3907   0.01813   0.00879  -0.0816   0.8056   0.1154
   0.000   0.4178   0.01780   0.00838  -0.0807   0.7954   0.1255
   0.250   0.4435   0.01744   0.00817  -0.0800   0.7830   0.1640
   0.500   0.4765   0.01525   0.00800  -0.0799   0.7716   1.0000
   0.750   0.5022   0.01540   0.00787  -0.0790   0.7599   1.0000
   1.000   0.5282   0.01549   0.00774  -0.0781   0.7489   1.0000
   1.250   0.5537   0.01561   0.00770  -0.0773   0.7366   1.0000
   1.500   0.5792   0.01575   0.00773  -0.0765   0.7237   1.0000
   1.750   0.6048   0.01588   0.00774  -0.0758   0.7109   1.0000
   2.000   0.6306   0.01599   0.00774  -0.0751   0.6980   1.0000
   2.250   0.6566   0.01611   0.00776  -0.0743   0.6850   1.0000
   2.500   0.6826   0.01623   0.00777  -0.0736   0.6717   1.0000
   2.750   0.7087   0.01639   0.00783  -0.0729   0.6579   1.0000
   3.000   0.7347   0.01658   0.00793  -0.0722   0.6436   1.0000
   3.250   0.7605   0.01682   0.00810  -0.0716   0.6285   1.0000
   3.500   0.7861   0.01710   0.00830  -0.0710   0.6127   1.0000
   3.750   0.8117   0.01740   0.00854  -0.0703   0.5964   1.0000
   4.000   0.8372   0.01772   0.00883  -0.0697   0.5801   1.0000
   4.250   0.8627   0.01805   0.00912  -0.0692   0.5643   1.0000
   4.500   0.8882   0.01838   0.00942  -0.0687   0.5489   1.0000
   4.750   0.9137   0.01868   0.00970  -0.0682   0.5338   1.0000
   5.000   0.9392   0.01897   0.00999  -0.0676   0.5191   1.0000
   5.250   0.9646   0.01926   0.01027  -0.0671   0.5049   1.0000
   5.500   0.9901   0.01956   0.01056  -0.0667   0.4916   1.0000
   5.750   1.0157   0.01988   0.01088  -0.0662   0.4792   1.0000
   6.000   1.0417   0.02019   0.01114  -0.0658   0.4675   1.0000
   6.250   1.0664   0.02062   0.01165  -0.0653   0.4551   1.0000
   6.500   1.0910   0.02112   0.01223  -0.0649   0.4438   1.0000
   6.750   1.1160   0.02160   0.01277  -0.0645   0.4330   1.0000
   7.000   1.1420   0.02204   0.01317  -0.0642   0.4231   1.0000
   7.250   1.1658   0.02259   0.01386  -0.0636   0.4121   1.0000
   7.500   1.1895   0.02315   0.01455  -0.0631   0.4012   1.0000
   7.750   1.2136   0.02365   0.01512  -0.0626   0.3899   1.0000
   8.000   1.2379   0.02412   0.01560  -0.0620   0.3783   1.0000
   8.250   1.2607   0.02452   0.01603  -0.0612   0.3645   1.0000
   8.500   1.2815   0.02490   0.01650  -0.0602   0.3491   1.0000
   8.750   1.3012   0.02530   0.01703  -0.0590   0.3335   1.0000
   9.000   1.3198   0.02570   0.01756  -0.0577   0.3174   1.0000
   9.250   1.3366   0.02606   0.01807  -0.0561   0.3002   1.0000
   9.500   1.3525   0.02646   0.01861  -0.0545   0.2831   1.0000
   9.750   1.3654   0.02681   0.01907  -0.0524   0.2635   1.0000
  10.000   1.3749   0.02729   0.01979  -0.0500   0.2394   1.0000
  10.250   1.3797   0.02805   0.02062  -0.0471   0.2055   1.0000
  10.500   1.3701   0.02995   0.02220  -0.0429   0.1422   1.0000
  10.750   1.3491   0.03318   0.02503  -0.0381   0.1045   1.0000
  11.000   1.3341   0.03651   0.02820  -0.0349   0.0798   1.0000
  11.250   1.3235   0.03974   0.03139  -0.0328   0.0701   1.0000
  11.500   1.3110   0.04339   0.03497  -0.0314   0.0653   1.0000
  11.750   1.3040   0.04676   0.03849  -0.0304   0.0609   1.0000
  12.000   1.2960   0.05035   0.04215  -0.0298   0.0576   1.0000
  12.250   1.2869   0.05403   0.04577  -0.0289   0.0547   1.0000
  12.500   1.2875   0.05685   0.04874  -0.0280   0.0520   1.0000
  12.750   1.2908   0.05935   0.05133  -0.0268   0.0496   1.0000
  13.000   1.2975   0.06150   0.05353  -0.0253   0.0475   1.0000
  13.250   1.3128   0.06298   0.05492  -0.0228   0.0452   1.0000
  13.500   1.3329   0.06492   0.05693  -0.0203   0.0434   1.0000
  13.750   1.3342   0.06804   0.06033  -0.0199   0.0424   1.0000
  14.000   1.3338   0.07143   0.06397  -0.0196   0.0413   1.0000
  14.250   1.3315   0.07512   0.06791  -0.0195   0.0404   1.0000
  14.500   1.3274   0.07914   0.07217  -0.0197   0.0398   1.0000
  14.750   1.3201   0.08364   0.07693  -0.0202   0.0396   1.0000
  15.000   1.3089   0.08868   0.08223  -0.0213   0.0395   1.0000
  15.250   1.2942   0.09427   0.08809  -0.0230   0.0396   1.0000
  15.500   1.2765   0.10049   0.09457  -0.0254   0.0398   1.0000
  15.750   1.2563   0.10745   0.10178  -0.0288   0.0400   1.0000
  16.000   1.2342   0.11521   0.10977  -0.0330   0.0404   1.0000
  16.250   1.2101   0.12390   0.11869  -0.0383   0.0408   1.0000
  16.500   1.1844   0.13365   0.12864  -0.0446   0.0414   1.0000
  16.750   1.1570   0.14466   0.13981  -0.0519   0.0421   1.0000
  17.000   1.1304   0.15644   0.15170  -0.0597   0.0430   1.0000
  17.250   1.1106   0.16720   0.16250  -0.0661   0.0438   1.0000
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