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GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 769 AIRFOIL (goe769-il)
Reynolds number: 100,000
Max Cl/Cd: 39.11 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe769-il-100000.txt
Download as CSV file: xf-goe769-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 769 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1977   0.09965   0.09508  -0.0234   1.0000   0.1123
  -8.000  -0.2249   0.09944   0.09504  -0.0271   1.0000   0.1148
  -7.750  -0.2634   0.09998   0.09587  -0.0272   1.0000   0.1152
  -7.500  -0.2576   0.09691   0.09294  -0.0235   0.9984   0.1159
  -7.250  -0.2068   0.09163   0.08766  -0.0236   0.9914   0.1191
  -7.000  -0.1725   0.08727   0.08330  -0.0314   0.9708   0.1245
  -6.750  -0.1577   0.08178   0.07776  -0.0498   0.9404   0.1296
  -6.500  -0.1161   0.07763   0.07361  -0.0489   0.9262   0.1321
  -6.250  -0.0849   0.07396   0.06987  -0.0535   0.9041   0.1371
  -6.000  -0.0859   0.06992   0.06559  -0.0676   0.8757   0.1444
  -5.750  -0.0622   0.06687   0.06255  -0.0644   0.8569   0.1463
  -5.500  -0.0443   0.06461   0.06023  -0.0631   0.8375   0.1496
  -5.250  -0.0448   0.06202   0.05729  -0.0720   0.8183   0.1607
  -5.000  -0.0278   0.05909   0.05445  -0.0686   0.8010   0.1627
  -4.750  -0.0115   0.05727   0.05262  -0.0661   0.7843   0.1668
  -4.500  -0.0016   0.05470   0.04978  -0.0702   0.7696   0.1796
  -4.250   0.0156   0.05260   0.04767  -0.0676   0.7556   0.1831
  -4.000   0.0301   0.05064   0.04546  -0.0701   0.7401   0.1982
  -3.750   0.0471   0.04840   0.04326  -0.0680   0.7257   0.2016
  -3.500   0.0745   0.03623   0.02949  -0.0762   0.7188   0.1166
  -3.250   0.0968   0.03397   0.02695  -0.0754   0.7053   0.1130
  -3.000   0.1199   0.03181   0.02436  -0.0746   0.6937   0.1125
  -2.750   0.1429   0.02991   0.02210  -0.0737   0.6792   0.1123
  -2.500   0.1675   0.02825   0.02002  -0.0727   0.6668   0.1126
  -2.250   0.1932   0.02693   0.01818  -0.0716   0.6544   0.1146
  -2.000   0.2174   0.02593   0.01716  -0.0708   0.6404   0.1191
  -1.750   0.2437   0.02518   0.01615  -0.0698   0.6286   0.1248
  -1.500   0.2696   0.02421   0.01492  -0.0688   0.6150   0.1306
  -1.250   0.2952   0.02370   0.01436  -0.0679   0.6021   0.1399
  -1.000   0.3219   0.02296   0.01347  -0.0670   0.5913   0.1507
  -0.750   0.3473   0.02243   0.01293  -0.0662   0.5782   0.1643
  -0.500   0.3741   0.02196   0.01235  -0.0653   0.5682   0.1809
  -0.250   0.3995   0.02158   0.01203  -0.0645   0.5559   0.1991
   0.000   0.4255   0.02124   0.01172  -0.0637   0.5456   0.2193
   0.250   0.4513   0.02088   0.01143  -0.0628   0.5348   0.2424
   0.500   0.4767   0.02061   0.01126  -0.0619   0.5242   0.2723
   0.750   0.5031   0.02009   0.01093  -0.0611   0.5144   0.3242
   1.000   0.5666   0.01809   0.01061  -0.0667   0.4999   1.0000
   1.250   0.5925   0.01830   0.01047  -0.0657   0.4911   1.0000
   1.500   0.6160   0.01859   0.01062  -0.0646   0.4797   1.0000
   1.750   0.6413   0.01886   0.01065  -0.0637   0.4705   1.0000
   2.000   0.6654   0.01915   0.01079  -0.0627   0.4598   1.0000
   2.250   0.6901   0.01950   0.01097  -0.0618   0.4503   1.0000
   2.500   0.7146   0.01980   0.01112  -0.0609   0.4401   1.0000
   2.750   0.7388   0.02022   0.01140  -0.0600   0.4304   1.0000
   3.000   0.7637   0.02055   0.01157  -0.0591   0.4208   1.0000
   3.250   0.7876   0.02104   0.01198  -0.0582   0.4115   1.0000
   3.500   0.8124   0.02141   0.01221  -0.0574   0.4023   1.0000
   3.750   0.8362   0.02194   0.01265  -0.0565   0.3935   1.0000
   4.000   0.8603   0.02236   0.01299  -0.0557   0.3847   1.0000
   4.250   0.8852   0.02292   0.01340  -0.0550   0.3771   1.0000
   4.500   0.9074   0.02346   0.01398  -0.0540   0.3685   1.0000
   4.750   0.9350   0.02391   0.01415  -0.0536   0.3621   1.0000
   5.000   0.9545   0.02463   0.01503  -0.0524   0.3538   1.0000
   5.250   0.9795   0.02509   0.01538  -0.0517   0.3473   1.0000
   5.500   1.0037   0.02579   0.01598  -0.0510   0.3413   1.0000
   5.750   1.0237   0.02652   0.01683  -0.0499   0.3341   1.0000
   6.000   1.0495   0.02698   0.01715  -0.0494   0.3286   1.0000
   6.250   1.0717   0.02782   0.01798  -0.0486   0.3231   1.0000
   6.500   1.0906   0.02869   0.01897  -0.0474   0.3169   1.0000
   6.750   1.1151   0.02923   0.01942  -0.0468   0.3119   1.0000
   7.000   1.1401   0.03000   0.02009  -0.0463   0.3073   1.0000
   7.250   1.1544   0.03114   0.02146  -0.0448   0.3016   1.0000
   7.500   1.1755   0.03190   0.02224  -0.0439   0.2968   1.0000
   7.750   1.2025   0.03246   0.02265  -0.0436   0.2929   1.0000
   8.000   1.2176   0.03380   0.02414  -0.0423   0.2886   1.0000
   8.250   1.2302   0.03511   0.02564  -0.0407   0.2837   1.0000
   8.500   1.2506   0.03590   0.02643  -0.0398   0.2795   1.0000
   8.750   1.2784   0.03646   0.02686  -0.0397   0.2761   1.0000
   9.000   1.2877   0.03824   0.02883  -0.0379   0.2725   1.0000
   9.250   1.2888   0.04030   0.03117  -0.0355   0.2685   1.0000
   9.500   1.3015   0.04161   0.03256  -0.0341   0.2647   1.0000
   9.750   1.3260   0.04220   0.03309  -0.0337   0.2614   1.0000
  10.000   1.3566   0.04297   0.03370  -0.0340   0.2584   1.0000
  10.250   1.3261   0.04675   0.03797  -0.0294   0.2555   1.0000
  10.500   1.2706   0.05186   0.04346  -0.0237   0.2532   1.0000
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