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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 100,000
Max Cl/Cd: 62.13 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe240-il-100000.txt
Download as CSV file: xf-goe240-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3235   0.10386   0.09914  -0.0280   1.0000   0.0589
  -7.750  -0.3309   0.10348   0.09887  -0.0303   1.0000   0.0593
  -7.500  -0.3320   0.10262   0.09809  -0.0344   1.0000   0.0596
  -7.250  -0.3255   0.09574   0.09126  -0.0285   1.0000   0.0607
  -7.000  -0.3184   0.09181   0.08736  -0.0249   1.0000   0.0629
  -6.750  -0.3182   0.08957   0.08519  -0.0239   1.0000   0.0651
  -6.500  -0.3205   0.08768   0.08337  -0.0234   1.0000   0.0672
  -6.250  -0.3249   0.08619   0.08197  -0.0233   1.0000   0.0693
  -6.000  -0.3293   0.08561   0.08144  -0.0254   1.0000   0.0711
  -5.750  -0.3206   0.08592   0.08164  -0.0337   1.0000   0.0722
  -5.500  -0.3211   0.08165   0.07745  -0.0318   1.0000   0.0728
  -5.250  -0.3247   0.07790   0.07378  -0.0269   1.0000   0.0739
  -5.000  -0.3230   0.07515   0.07107  -0.0246   1.0000   0.0755
  -4.750  -0.3160   0.07262   0.06854  -0.0245   1.0000   0.0780
  -4.500  -0.3022   0.07001   0.06588  -0.0269   1.0000   0.0819
  -4.250  -0.2547   0.06538   0.06105  -0.0385   0.9957   0.0874
  -4.000  -0.2282   0.06168   0.05734  -0.0406   0.9906   0.0932
  -3.750  -0.1736   0.05723   0.05261  -0.0517   0.9849   0.1016
  -3.500  -0.1423   0.05388   0.04921  -0.0549   0.9791   0.1079
  -3.250  -0.0955   0.05008   0.04519  -0.0623   0.9732   0.1173
  -3.000  -0.0530   0.04698   0.04190  -0.0680   0.9676   0.1313
  -2.750  -0.0126   0.04418   0.03890  -0.0727   0.9607   0.1458
  -2.500   0.0318   0.04133   0.03591  -0.0778   0.9563   0.1624
  -2.250   0.0684   0.03968   0.03401  -0.0811   0.9476   0.1889
  -2.000   0.1078   0.03700   0.03133  -0.0847   0.9428   0.2203
  -1.750   0.1368   0.03514   0.02947  -0.0860   0.9340   0.2553
  -1.000   0.3049   0.02713   0.01929  -0.0997   0.9161   0.1160
  -0.750   0.3479   0.02561   0.01744  -0.1019   0.9076   0.1099
  -0.500   0.4007   0.02374   0.01513  -0.1054   0.9008   0.1023
  -0.250   0.4408   0.02258   0.01372  -0.1067   0.8899   0.1008
   0.000   0.4824   0.02127   0.01236  -0.1084   0.8816   0.1027
   0.250   0.5201   0.02026   0.01137  -0.1095   0.8727   0.1085
   0.500   0.5522   0.01945   0.01063  -0.1096   0.8619   0.1192
   0.750   0.5864   0.01858   0.00980  -0.1098   0.8526   0.1348
   1.000   0.6225   0.01585   0.00898  -0.1103   0.8438   1.0000
   1.250   0.6517   0.01582   0.00866  -0.1097   0.8310   1.0000
   1.500   0.6803   0.01583   0.00850  -0.1090   0.8180   1.0000
   1.750   0.7082   0.01587   0.00840  -0.1083   0.8046   1.0000
   2.000   0.7353   0.01597   0.00839  -0.1074   0.7907   1.0000
   2.250   0.7616   0.01611   0.00843  -0.1065   0.7762   1.0000
   2.500   0.7872   0.01623   0.00848  -0.1054   0.7605   1.0000
   2.750   0.8124   0.01628   0.00845  -0.1041   0.7434   1.0000
   3.000   0.8377   0.01624   0.00831  -0.1027   0.7254   1.0000
   3.250   0.8628   0.01615   0.00813  -0.1012   0.7066   1.0000
   3.500   0.8863   0.01613   0.00808  -0.0997   0.6851   1.0000
   3.750   0.9114   0.01610   0.00799  -0.0985   0.6660   1.0000
   4.000   0.9367   0.01611   0.00795  -0.0975   0.6475   1.0000
   4.250   0.9609   0.01621   0.00806  -0.0964   0.6262   1.0000
   4.500   0.9860   0.01629   0.00807  -0.0953   0.6061   1.0000
   4.750   1.0103   0.01647   0.00821  -0.0943   0.5833   1.0000
   5.000   1.0348   0.01668   0.00828  -0.0931   0.5604   1.0000
   5.250   1.0580   0.01703   0.00858  -0.0920   0.5344   1.0000
   5.500   1.0809   0.01745   0.00891  -0.0908   0.5083   1.0000
   5.750   1.1032   0.01789   0.00927  -0.0896   0.4819   1.0000
   6.000   1.1251   0.01832   0.00962  -0.0884   0.4553   1.0000
   6.250   1.1464   0.01876   0.01007  -0.0871   0.4282   1.0000
   6.500   1.1675   0.01926   0.01055  -0.0859   0.4015   1.0000
   6.750   1.1884   0.01988   0.01110  -0.0846   0.3765   1.0000
   7.000   1.2093   0.02063   0.01171  -0.0834   0.3541   1.0000
   7.250   1.2299   0.02143   0.01252  -0.0823   0.3319   1.0000
   7.500   1.2502   0.02222   0.01325  -0.0811   0.3121   1.0000
   7.750   1.2697   0.02296   0.01396  -0.0799   0.2932   1.0000
   8.000   1.2883   0.02359   0.01468  -0.0785   0.2747   1.0000
   8.250   1.3072   0.02423   0.01540  -0.0772   0.2587   1.0000
   8.500   1.3262   0.02488   0.01619  -0.0760   0.2449   1.0000
   8.750   1.3423   0.02543   0.01685  -0.0743   0.2273   1.0000
   9.000   1.3562   0.02605   0.01751  -0.0725   0.2065   1.0000
   9.250   1.3700   0.02679   0.01839  -0.0706   0.1845   1.0000
   9.500   1.3780   0.02797   0.01955  -0.0681   0.1471   1.0000
   9.750   1.3755   0.03037   0.02141  -0.0643   0.0770   1.0000
  10.000   1.3680   0.03292   0.02370  -0.0600   0.0643   1.0000
  10.250   1.3638   0.03528   0.02617  -0.0564   0.0580   1.0000
  10.500   1.3556   0.03804   0.02895  -0.0530   0.0544   1.0000
  10.750   1.3555   0.04039   0.03145  -0.0503   0.0518   1.0000
  11.000   1.3582   0.04269   0.03390  -0.0480   0.0493   1.0000
  11.250   1.3628   0.04504   0.03634  -0.0459   0.0471   1.0000
  11.500   1.3703   0.04746   0.03878  -0.0441   0.0450   1.0000
  11.750   1.3917   0.05060   0.04182  -0.0426   0.0422   1.0000
  12.000   1.3955   0.05281   0.04433  -0.0409   0.0409   1.0000
  12.250   1.4020   0.05540   0.04721  -0.0394   0.0396   1.0000
  12.500   1.4092   0.05838   0.05046  -0.0379   0.0389   1.0000
  12.750   1.4118   0.06169   0.05406  -0.0364   0.0384   1.0000
  13.000   1.4096   0.06532   0.05798  -0.0352   0.0382   1.0000
  13.250   1.4028   0.06928   0.06225  -0.0342   0.0381   1.0000
  13.500   1.3919   0.07363   0.06690  -0.0336   0.0382   1.0000
  13.750   1.3774   0.07840   0.07196  -0.0336   0.0383   1.0000
  14.000   1.3603   0.08362   0.07746  -0.0343   0.0385   1.0000
  14.250   1.3409   0.08936   0.08347  -0.0357   0.0387   1.0000
  14.500   1.3197   0.09567   0.09003  -0.0380   0.0390   1.0000
  14.750   1.2973   0.10259   0.09719  -0.0412   0.0393   1.0000
  15.000   1.2737   0.11026   0.10507  -0.0454   0.0397   1.0000
  15.250   1.2494   0.11879   0.11379  -0.0506   0.0401   1.0000
  15.500   1.2244   0.12831   0.12348  -0.0568   0.0406   1.0000
  15.750   1.1993   0.13880   0.13411  -0.0639   0.0412   1.0000
  16.000   1.1767   0.14961   0.14499  -0.0708   0.0419   1.0000
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