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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 50,000
Max Cl/Cd: 43.51 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe240-il-50000-n5.txt
Download as CSV file: xf-goe240-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) AIRFOIL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3080   0.10088   0.09443  -0.0263   1.0000   0.0839
  -7.250  -0.3106   0.09899   0.09265  -0.0262   1.0000   0.0860
  -7.000  -0.3142   0.09766   0.09144  -0.0275   1.0000   0.0883
  -6.750  -0.3176   0.09695   0.09085  -0.0306   1.0000   0.0895
  -6.500  -0.3173   0.09614   0.09009  -0.0346   1.0000   0.0901
  -6.250  -0.3150   0.09021   0.08428  -0.0268   1.0000   0.0930
  -6.000  -0.3147   0.08779   0.08193  -0.0253   1.0000   0.0960
  -5.750  -0.3148   0.08575   0.07994  -0.0252   1.0000   0.0990
  -5.500  -0.3117   0.08409   0.07830  -0.0279   1.0000   0.1026
  -5.250  -0.2977   0.08294   0.07703  -0.0354   1.0000   0.1042
  -5.000  -0.2982   0.07875   0.07297  -0.0314   1.0000   0.1055
  -4.750  -0.2800   0.07469   0.06890  -0.0323   0.9958   0.1089
  -4.500  -0.2339   0.07046   0.06445  -0.0438   0.9873   0.1195
  -4.250  -0.1946   0.06673   0.06051  -0.0513   0.9793   0.1331
  -4.000  -0.1710   0.06248   0.05628  -0.0523   0.9728   0.1389
  -3.750  -0.1326   0.05877   0.05239  -0.0587   0.9655   0.1515
  -3.500  -0.1015   0.05566   0.04917  -0.0623   0.9580   0.1691
  -3.250  -0.0215   0.04905   0.04150  -0.0764   0.9524   0.0897
  -3.000   0.0078   0.04561   0.03799  -0.0786   0.9456   0.0838
  -2.750   0.0580   0.04181   0.03341  -0.0842   0.9393   0.0754
  -2.500   0.0934   0.03929   0.03072  -0.0872   0.9331   0.0784
  -2.250   0.1289   0.03716   0.02827  -0.0897   0.9254   0.0796
  -2.000   0.1756   0.03467   0.02505  -0.0934   0.9206   0.0769
  -1.750   0.2085   0.03314   0.02303  -0.0945   0.9114   0.0761
  -1.500   0.2504   0.03141   0.02090  -0.0974   0.9062   0.0761
  -1.250   0.2815   0.03014   0.01937  -0.0982   0.8969   0.0767
  -1.000   0.3201   0.02897   0.01803  -0.1004   0.8906   0.0800
  -0.750   0.3532   0.02818   0.01702  -0.1014   0.8817   0.0850
  -0.500   0.3881   0.02735   0.01587  -0.1023   0.8736   0.0878
  -0.250   0.4259   0.02655   0.01475  -0.1035   0.8662   0.0903
   0.000   0.4582   0.02586   0.01399  -0.1040   0.8568   0.0942
   0.250   0.4951   0.02515   0.01314  -0.1051   0.8491   0.1008
   0.500   0.5281   0.02454   0.01248  -0.1055   0.8384   0.1109
   0.750   0.5604   0.02391   0.01194  -0.1059   0.8265   0.1379
   1.000   0.5904   0.02146   0.01159  -0.1059   0.8150   1.0000
   1.250   0.6222   0.02147   0.01117  -0.1057   0.8026   1.0000
   1.500   0.6539   0.02148   0.01091  -0.1057   0.7909   1.0000
   1.750   0.6825   0.02161   0.01086  -0.1053   0.7780   1.0000
   2.000   0.7091   0.02182   0.01095  -0.1046   0.7643   1.0000
   2.250   0.7354   0.02203   0.01106  -0.1040   0.7505   1.0000
   2.500   0.7615   0.02225   0.01120  -0.1033   0.7366   1.0000
   2.750   0.7872   0.02246   0.01138  -0.1025   0.7224   1.0000
   3.000   0.8127   0.02268   0.01156  -0.1017   0.7080   1.0000
   3.250   0.8379   0.02289   0.01175  -0.1008   0.6932   1.0000
   3.500   0.8629   0.02309   0.01198  -0.0999   0.6780   1.0000
   3.750   0.8877   0.02328   0.01218  -0.0990   0.6623   1.0000
   4.000   0.9125   0.02343   0.01233  -0.0979   0.6457   1.0000
   4.250   0.9376   0.02343   0.01234  -0.0967   0.6269   1.0000
   4.500   0.9597   0.02354   0.01246  -0.0951   0.6036   1.0000
   4.750   0.9839   0.02353   0.01239  -0.0936   0.5806   1.0000
   5.000   1.0073   0.02367   0.01248  -0.0922   0.5570   1.0000
   5.250   1.0312   0.02393   0.01271  -0.0910   0.5356   1.0000
   5.500   1.0541   0.02433   0.01311  -0.0898   0.5143   1.0000
   5.750   1.0773   0.02476   0.01352  -0.0887   0.4938   1.0000
   6.000   1.0987   0.02531   0.01414  -0.0875   0.4721   1.0000
   6.250   1.1201   0.02588   0.01480  -0.0863   0.4511   1.0000
   6.500   1.1410   0.02647   0.01544  -0.0851   0.4304   1.0000
   6.750   1.1608   0.02713   0.01619  -0.0838   0.4089   1.0000
   7.000   1.1805   0.02778   0.01684  -0.0823   0.3885   1.0000
   7.250   1.1993   0.02853   0.01770  -0.0809   0.3680   1.0000
   7.500   1.2180   0.02934   0.01856  -0.0795   0.3491   1.0000
   7.750   1.2366   0.03021   0.01948  -0.0781   0.3319   1.0000
   8.000   1.2554   0.03114   0.02049  -0.0768   0.3162   1.0000
   8.250   1.2742   0.03212   0.02161  -0.0756   0.3020   1.0000
   8.500   1.2925   0.03314   0.02284  -0.0743   0.2885   1.0000
   8.750   1.3054   0.03412   0.02392  -0.0724   0.2712   1.0000
   9.000   1.3135   0.03513   0.02500  -0.0700   0.2515   1.0000
   9.250   1.3206   0.03626   0.02628  -0.0676   0.2323   1.0000
   9.500   1.3279   0.03745   0.02762  -0.0653   0.2160   1.0000
   9.750   1.3335   0.03873   0.02905  -0.0628   0.2016   1.0000
  10.000   1.3340   0.04031   0.03069  -0.0602   0.1836   1.0000
  10.250   1.3323   0.04228   0.03275  -0.0578   0.1619   1.0000
  10.500   1.3297   0.04461   0.03514  -0.0559   0.1399   1.0000
  10.750   1.3261   0.04737   0.03798  -0.0544   0.1081   1.0000
  11.000   1.3187   0.05081   0.04130  -0.0532   0.0731   1.0000
  11.250   1.3054   0.05510   0.04534  -0.0524   0.0644   1.0000
  11.500   1.2936   0.05952   0.04977  -0.0519   0.0584   1.0000
  11.750   1.2818   0.06416   0.05451  -0.0519   0.0542   1.0000
  12.000   1.2682   0.06920   0.05961  -0.0523   0.0513   1.0000
  12.250   1.2586   0.07393   0.06451  -0.0527   0.0483   1.0000
  12.500   1.2502   0.07863   0.06943  -0.0533   0.0455   1.0000
  12.750   1.2414   0.08349   0.07446  -0.0542   0.0435   1.0000
  13.000   1.2327   0.08839   0.07949  -0.0551   0.0420   1.0000
  13.250   1.2243   0.09325   0.08445  -0.0561   0.0407   1.0000
  13.500   1.2196   0.09768   0.08904  -0.0568   0.0394   1.0000
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