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GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 367 AIRFOIL (goe367-il)
Reynolds number: 100,000
Max Cl/Cd: 47.66 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe367-il-100000-n5.txt
Download as CSV file: xf-goe367-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 367 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2225   0.09515   0.08966  -0.0832   0.9611   0.0605
 -10.000  -0.2175   0.08998   0.08448  -0.0879   0.9557   0.0610
  -9.750  -0.2184   0.08469   0.07917  -0.0921   0.9476   0.0611
  -9.500  -0.2226   0.07813   0.07261  -0.0981   0.9401   0.0610
  -9.250  -0.2493   0.06877   0.06320  -0.1065   0.9268   0.0602
  -9.000  -0.2951   0.05966   0.05382  -0.1097   0.9115   0.0596
  -8.750  -0.3180   0.05305   0.04685  -0.1100   0.9022   0.0596
  -8.500  -0.3312   0.04858   0.04203  -0.1081   0.8918   0.0599
  -8.250  -0.3290   0.04478   0.03783  -0.1073   0.8859   0.0608
  -8.000  -0.3307   0.04195   0.03465  -0.1045   0.8761   0.0618
  -7.750  -0.3230   0.03843   0.03056  -0.1032   0.8707   0.0632
  -7.500  -0.3177   0.03578   0.02737  -0.1005   0.8623   0.0642
  -7.250  -0.2995   0.03399   0.02530  -0.0995   0.8563   0.0650
  -7.000  -0.2739   0.03275   0.02392  -0.0996   0.8523   0.0659
  -6.750  -0.2569   0.03184   0.02289  -0.0981   0.8448   0.0669
  -6.500  -0.2345   0.03083   0.02170  -0.0974   0.8390   0.0684
  -6.250  -0.2085   0.02957   0.02017  -0.0973   0.8350   0.0706
  -6.000  -0.1882   0.02841   0.01867  -0.0961   0.8287   0.0725
  -5.750  -0.1652   0.02774   0.01799  -0.0954   0.8225   0.0739
  -5.500  -0.1375   0.02698   0.01716  -0.0955   0.8182   0.0755
  -5.250  -0.1106   0.02624   0.01630  -0.0953   0.8136   0.0778
  -5.000  -0.0898   0.02567   0.01557  -0.0941   0.8062   0.0806
  -4.750  -0.0626   0.02507   0.01494  -0.0940   0.8014   0.0833
  -4.500  -0.0323   0.02447   0.01429  -0.0943   0.7977   0.0864
  -4.250  -0.0124   0.02410   0.01385  -0.0929   0.7898   0.0896
  -4.000   0.0141   0.02361   0.01332  -0.0926   0.7843   0.0935
  -3.750   0.0441   0.02312   0.01279  -0.0929   0.7802   0.0987
  -3.500   0.0656   0.02281   0.01243  -0.0917   0.7728   0.1039
  -3.250   0.0910   0.02246   0.01211  -0.0913   0.7667   0.1097
  -3.000   0.1209   0.02196   0.01155  -0.0914   0.7623   0.1184
  -2.750   0.1422   0.02177   0.01140  -0.0903   0.7546   0.1268
  -2.500   0.1676   0.02142   0.01105  -0.0898   0.7482   0.1365
  -2.250   0.1979   0.02099   0.01056  -0.0900   0.7435   0.1487
  -2.000   0.2177   0.02087   0.01048  -0.0886   0.7348   0.1588
  -1.750   0.2445   0.02051   0.01014  -0.0883   0.7284   0.1707
  -1.500   0.2714   0.02022   0.00983  -0.0880   0.7220   0.1837
  -1.250   0.2936   0.02005   0.00972  -0.0869   0.7133   0.1997
  -1.000   0.3230   0.01959   0.00934  -0.0871   0.7074   0.2243
  -0.500   0.3685   0.01863   0.00908  -0.0853   0.6909   0.3771
  -0.250   0.4125   0.01764   0.00969  -0.0867   0.6833   0.8420
   0.000   0.4401   0.01786   0.00982  -0.0857   0.6751   0.9176
   0.250   0.5028   0.01804   0.00982  -0.0920   0.6674   0.9583
   0.500   0.5806   0.01806   0.00969  -0.1020   0.6578   0.9849
   0.750   0.6441   0.01796   0.00942  -0.1094   0.6492   1.0000
   1.000   0.6641   0.01803   0.00941  -0.1080   0.6400   1.0000
   1.250   0.6851   0.01809   0.00936  -0.1068   0.6317   1.0000
   1.500   0.7047   0.01818   0.00938  -0.1054   0.6224   1.0000
   1.750   0.7250   0.01826   0.00937  -0.1040   0.6137   1.0000
   2.000   0.7446   0.01836   0.00940  -0.1026   0.6047   1.0000
   2.250   0.7641   0.01849   0.00945  -0.1011   0.5960   1.0000
   2.500   0.7837   0.01861   0.00949  -0.0996   0.5874   1.0000
   2.750   0.8031   0.01876   0.00957  -0.0981   0.5793   1.0000
   3.000   0.8218   0.01892   0.00967  -0.0964   0.5709   1.0000
   3.250   0.8414   0.01907   0.00975  -0.0949   0.5631   1.0000
   3.500   0.8587   0.01928   0.00992  -0.0931   0.5545   1.0000
   3.750   0.8791   0.01944   0.00998  -0.0917   0.5472   1.0000
   4.000   0.8946   0.01971   0.01023  -0.0895   0.5386   1.0000
   4.250   0.9162   0.01986   0.01029  -0.0884   0.5319   1.0000
   4.500   0.9303   0.02018   0.01062  -0.0860   0.5239   1.0000
   4.750   0.9491   0.02042   0.01080  -0.0844   0.5172   1.0000
   5.000   0.9680   0.02069   0.01103  -0.0829   0.5108   1.0000
   5.250   0.9829   0.02102   0.01137  -0.0807   0.5038   1.0000
   5.500   1.0036   0.02127   0.01156  -0.0795   0.4980   1.0000
   5.750   1.0200   0.02162   0.01191  -0.0776   0.4917   1.0000
   6.000   1.0351   0.02196   0.01227  -0.0755   0.4846   1.0000
   6.250   1.0580   0.02220   0.01242  -0.0747   0.4786   1.0000
   6.500   1.0686   0.02265   0.01293  -0.0719   0.4710   1.0000
   6.750   1.0863   0.02298   0.01324  -0.0702   0.4643   1.0000
   7.000   1.1051   0.02333   0.01357  -0.0689   0.4582   1.0000
   7.250   1.1180   0.02379   0.01409  -0.0666   0.4515   1.0000
   7.500   1.1371   0.02413   0.01442  -0.0653   0.4458   1.0000
   7.750   1.1535   0.02456   0.01486  -0.0636   0.4403   1.0000
   8.000   1.1649   0.02508   0.01545  -0.0611   0.4341   1.0000
   8.250   1.1831   0.02546   0.01583  -0.0598   0.4285   1.0000
   8.500   1.1976   0.02597   0.01638  -0.0580   0.4227   1.0000
   8.750   1.2086   0.02658   0.01707  -0.0557   0.4164   1.0000
   9.000   1.2270   0.02702   0.01753  -0.0545   0.4113   1.0000
   9.250   1.2438   0.02758   0.01813  -0.0532   0.4067   1.0000
   9.500   1.2542   0.02836   0.01904  -0.0512   0.4015   1.0000
   9.750   1.2692   0.02898   0.01973  -0.0497   0.3965   1.0000
  10.000   1.2913   0.02936   0.02009  -0.0492   0.3922   1.0000
  10.250   1.2966   0.03040   0.02130  -0.0467   0.3868   1.0000
  10.500   1.3064   0.03127   0.02228  -0.0448   0.3811   1.0000
  10.750   1.3247   0.03174   0.02275  -0.0439   0.3758   1.0000
  11.000   1.3289   0.03296   0.02412  -0.0416   0.3700   1.0000
  11.250   1.3364   0.03406   0.02534  -0.0398   0.3644   1.0000
  11.500   1.3520   0.03471   0.02603  -0.0387   0.3593   1.0000
  11.750   1.3551   0.03612   0.02760  -0.0367   0.3532   1.0000
  12.000   1.3578   0.03758   0.02918  -0.0347   0.3464   1.0000
  12.250   1.3722   0.03827   0.02987  -0.0336   0.3402   1.0000
  12.500   1.3656   0.04056   0.03239  -0.0314   0.3332   1.0000
  12.750   1.3709   0.04199   0.03391  -0.0299   0.3264   1.0000
  13.000   1.3701   0.04398   0.03602  -0.0283   0.3189   1.0000
  13.250   1.3663   0.04626   0.03842  -0.0267   0.3102   1.0000
  13.500   1.3598   0.04895   0.04124  -0.0253   0.3008   1.0000
  13.750   1.3576   0.05126   0.04358  -0.0241   0.2902   1.0000
  14.000   1.3391   0.05566   0.04819  -0.0230   0.2793   1.0000
  14.250   1.3240   0.05990   0.05256  -0.0224   0.2672   1.0000
  14.500   1.3063   0.06472   0.05749  -0.0220   0.2533   1.0000
  14.750   1.2875   0.06994   0.06280  -0.0220   0.2365   1.0000
  15.000   1.2758   0.07424   0.06706  -0.0221   0.2146   1.0000
  15.250   1.2664   0.07813   0.07075  -0.0220   0.1920   1.0000
  15.500   1.2529   0.08268   0.07512  -0.0221   0.1767   1.0000
  15.750   1.2400   0.08735   0.07970  -0.0224   0.1647   1.0000
  16.000   1.2297   0.09178   0.08410  -0.0228   0.1544   1.0000
  16.250   1.2209   0.09602   0.08829  -0.0233   0.1449   1.0000
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