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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 100,000
Max Cl/Cd: 59.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe602m-il-100000-n5.txt
Download as CSV file: xf-goe602m-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3669   0.09228   0.08758  -0.0373   1.0000   0.0288
  -8.250  -0.3753   0.08925   0.08464  -0.0369   1.0000   0.0284
  -8.000  -0.3873   0.08637   0.08186  -0.0359   1.0000   0.0279
  -7.750  -0.4029   0.08385   0.07945  -0.0342   1.0000   0.0276
  -7.500  -0.4208   0.08090   0.07661  -0.0331   1.0000   0.0270
  -7.250  -0.4328   0.07708   0.07288  -0.0338   1.0000   0.0267
  -7.000  -0.4412   0.07272   0.06858  -0.0357   1.0000   0.0265
  -6.750  -0.4307   0.06794   0.06377  -0.0408   0.9971   0.0273
  -6.500  -0.4061   0.05999   0.05568  -0.0517   0.9906   0.0283
  -6.250  -0.3803   0.05108   0.04643  -0.0622   0.9843   0.0292
  -6.000  -0.3537   0.04291   0.03769  -0.0701   0.9782   0.0298
  -5.750  -0.3264   0.03676   0.03083  -0.0746   0.9727   0.0309
  -5.500  -0.2953   0.03244   0.02565  -0.0777   0.9679   0.0339
  -5.250  -0.2635   0.02901   0.02144  -0.0798   0.9638   0.0364
  -5.000  -0.2354   0.02689   0.01906  -0.0809   0.9583   0.0391
  -4.750  -0.2014   0.02548   0.01731  -0.0826   0.9543   0.0443
  -4.500  -0.1701   0.02387   0.01525  -0.0833   0.9494   0.0471
  -4.250  -0.1400   0.02256   0.01382  -0.0842   0.9438   0.0520
  -4.000  -0.1047   0.02152   0.01261  -0.0858   0.9398   0.0558
  -3.750  -0.0750   0.02066   0.01158  -0.0861   0.9336   0.0589
  -3.500  -0.0425   0.01991   0.01075  -0.0872   0.9281   0.0643
  -3.250  -0.0051   0.01919   0.00995  -0.0891   0.9244   0.0688
  -3.000   0.0220   0.01868   0.00931  -0.0889   0.9160   0.0732
  -2.750   0.0590   0.01805   0.00864  -0.0906   0.9115   0.0827
  -2.500   0.0887   0.01750   0.00809  -0.0910   0.9039   0.1054
  -2.250   0.1234   0.01670   0.00755  -0.0925   0.8984   0.1684
  -2.000   0.1559   0.01616   0.00739  -0.0936   0.8918   0.2978
  -1.750   0.1868   0.01569   0.00722  -0.0943   0.8846   0.3856
  -1.500   0.2169   0.01532   0.00715  -0.0945   0.8772   0.4748
  -1.250   0.2482   0.01501   0.00699  -0.0949   0.8697   0.5519
  -1.000   0.2770   0.01473   0.00678  -0.0948   0.8610   0.6054
  -0.750   0.3081   0.01422   0.00656  -0.0948   0.8542   0.6856
  -0.500   0.3558   0.01355   0.00633  -0.0980   0.8465   1.0000
  -0.250   0.3904   0.01345   0.00605  -0.0991   0.8386   1.0000
   0.000   0.4181   0.01345   0.00592  -0.0989   0.8271   1.0000
   0.250   0.4465   0.01345   0.00579  -0.0989   0.8155   1.0000
   0.500   0.4759   0.01343   0.00566  -0.0990   0.8039   1.0000
   0.750   0.5061   0.01341   0.00553  -0.0992   0.7924   1.0000
   1.000   0.5366   0.01338   0.00541  -0.0994   0.7805   1.0000
   1.250   0.5664   0.01338   0.00532  -0.0995   0.7676   1.0000
   1.500   0.5951   0.01341   0.00528  -0.0995   0.7535   1.0000
   1.750   0.6238   0.01345   0.00526  -0.0994   0.7390   1.0000
   2.000   0.6523   0.01352   0.00525  -0.0992   0.7240   1.0000
   2.250   0.6798   0.01362   0.00530  -0.0989   0.7080   1.0000
   2.500   0.7067   0.01374   0.00537  -0.0986   0.6913   1.0000
   2.750   0.7333   0.01388   0.00547  -0.0981   0.6740   1.0000
   3.000   0.7597   0.01405   0.00560  -0.0976   0.6566   1.0000
   3.250   0.7859   0.01424   0.00574  -0.0971   0.6394   1.0000
   3.500   0.8118   0.01444   0.00590  -0.0965   0.6221   1.0000
   3.750   0.8364   0.01468   0.00612  -0.0958   0.6032   1.0000
   4.000   0.8609   0.01493   0.00637  -0.0950   0.5841   1.0000
   4.250   0.8852   0.01520   0.00660  -0.0941   0.5651   1.0000
   4.500   0.9090   0.01549   0.00689  -0.0932   0.5462   1.0000
   4.750   0.9324   0.01579   0.00723  -0.0923   0.5275   1.0000
   5.000   0.9559   0.01612   0.00757  -0.0914   0.5094   1.0000
   5.250   0.9789   0.01646   0.00792  -0.0904   0.4914   1.0000
   5.500   1.0014   0.01682   0.00833  -0.0894   0.4725   1.0000
   5.750   1.0213   0.01723   0.00873  -0.0878   0.4450   1.0000
   6.000   1.0369   0.01775   0.00907  -0.0855   0.4010   1.0000
   6.250   1.0516   0.01838   0.00949  -0.0833   0.3502   1.0000
   6.500   1.0675   0.01906   0.01001  -0.0813   0.3052   1.0000
   6.750   1.0816   0.01993   0.01064  -0.0791   0.2536   1.0000
   7.000   1.0919   0.02118   0.01147  -0.0766   0.1844   1.0000
   7.250   1.0990   0.02285   0.01263  -0.0738   0.1072   1.0000
   7.500   1.1053   0.02462   0.01396  -0.0709   0.0416   1.0000
   7.750   1.1152   0.02602   0.01525  -0.0683   0.0318   1.0000
   8.000   1.1239   0.02736   0.01668  -0.0654   0.0278   1.0000
   8.250   1.1341   0.02849   0.01798  -0.0628   0.0254   1.0000
   8.500   1.1432   0.02969   0.01938  -0.0601   0.0238   1.0000
   8.750   1.1505   0.03102   0.02089  -0.0574   0.0228   1.0000
   9.000   1.1561   0.03247   0.02252  -0.0546   0.0219   1.0000
   9.250   1.1598   0.03408   0.02430  -0.0518   0.0211   1.0000
   9.500   1.1619   0.03588   0.02625  -0.0491   0.0202   1.0000
   9.750   1.1621   0.03791   0.02841  -0.0466   0.0193   1.0000
  10.000   1.1605   0.04030   0.03091  -0.0441   0.0184   1.0000
  10.250   1.1609   0.04300   0.03373  -0.0418   0.0176   1.0000
  10.500   1.1700   0.04493   0.03580  -0.0403   0.0173   1.0000
  10.750   1.1805   0.04695   0.03796  -0.0389   0.0170   1.0000
  11.000   1.1921   0.04907   0.04024  -0.0376   0.0168   1.0000
  11.250   1.2037   0.05139   0.04275  -0.0363   0.0165   1.0000
  11.500   1.2139   0.05392   0.04548  -0.0351   0.0163   1.0000
  11.750   1.2204   0.05661   0.04842  -0.0339   0.0160   1.0000
  12.000   1.2231   0.05949   0.05155  -0.0328   0.0157   1.0000
  12.250   1.2225   0.06261   0.05494  -0.0319   0.0153   1.0000
  12.500   1.2189   0.06597   0.05856  -0.0312   0.0149   1.0000
  12.750   1.2133   0.06971   0.06255  -0.0309   0.0147   1.0000
  13.000   1.2054   0.07374   0.06684  -0.0310   0.0144   1.0000
  13.250   1.1956   0.07818   0.07153  -0.0316   0.0143   1.0000
  13.500   1.1838   0.08308   0.07668  -0.0327   0.0142   1.0000
  13.750   1.1706   0.08840   0.08224  -0.0345   0.0142   1.0000
  14.000   1.1560   0.09423   0.08831  -0.0369   0.0142   1.0000
  14.250   1.1404   0.10059   0.09489  -0.0399   0.0142   1.0000
  14.500   1.1241   0.10752   0.10203  -0.0437   0.0143   1.0000
  14.750   1.1070   0.11511   0.10982  -0.0482   0.0144   1.0000
  15.000   1.0896   0.12334   0.11823  -0.0533   0.0146   1.0000
  15.250   1.0717   0.13232   0.12738  -0.0591   0.0148   1.0000
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