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EPPLER 333 AIRFOIL (e333-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 333 AIRFOIL (e333-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.49 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e333-il-1000000-n5.txt
Download as CSV file: xf-e333-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 333 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3121   0.08200   0.07924  -0.0389   0.6627   0.0049
  -8.500  -0.3139   0.07816   0.07536  -0.0409   0.6471   0.0049
  -8.250  -0.3196   0.07397   0.07117  -0.0440   0.6369   0.0049
  -8.000  -0.3315   0.07044   0.06761  -0.0455   0.6268   0.0048
  -7.750  -0.3405   0.06738   0.06450  -0.0453   0.6167   0.0047
  -7.500  -0.3418   0.06413   0.06120  -0.0459   0.6072   0.0045
  -7.250  -0.3396   0.06093   0.05791  -0.0462   0.5966   0.0044
  -7.000  -0.3386   0.05691   0.05379  -0.0463   0.5880   0.0042
  -6.750  -0.3345   0.05300   0.04975  -0.0459   0.5796   0.0040
  -6.500  -0.3297   0.04864   0.04523  -0.0450   0.5718   0.0038
  -6.000  -0.3243   0.03640   0.03243  -0.0400   0.5601   0.0034
  -5.750  -0.3180   0.03047   0.02612  -0.0366   0.5539   0.0034
  -5.500  -0.3028   0.02712   0.02249  -0.0344   0.5465   0.0035
  -5.250  -0.2880   0.02303   0.01802  -0.0317   0.5393   0.0039
  -5.000  -0.2762   0.01679   0.01102  -0.0278   0.5332   0.0044
  -4.750  -0.2530   0.01520   0.00910  -0.0267   0.5242   0.0044
  -4.500  -0.2282   0.01423   0.00793  -0.0259   0.5152   0.0046
  -4.250  -0.2031   0.01340   0.00690  -0.0252   0.5068   0.0046
  -4.000  -0.1774   0.01279   0.00616  -0.0247   0.4991   0.0047
  -3.750  -0.1514   0.01239   0.00565  -0.0242   0.4912   0.0048
  -3.500  -0.1254   0.01199   0.00515  -0.0237   0.4827   0.0049
  -3.250  -0.1000   0.01153   0.00458  -0.0231   0.4754   0.0050
  -3.000  -0.0753   0.01095   0.00392  -0.0224   0.4681   0.0053
  -2.750  -0.0498   0.01063   0.00352  -0.0218   0.4614   0.0054
  -2.500  -0.0241   0.01032   0.00316  -0.0213   0.4545   0.0054
  -2.000   0.0278   0.00986   0.00259  -0.0203   0.4413   0.0057
  -1.750   0.0540   0.00968   0.00236  -0.0199   0.4351   0.0059
  -1.500   0.0805   0.00954   0.00218  -0.0195   0.4295   0.0061
  -1.250   0.1071   0.00942   0.00201  -0.0192   0.4231   0.0065
  -1.000   0.1337   0.00933   0.00187  -0.0188   0.4171   0.0073
  -0.750   0.1605   0.00920   0.00174  -0.0185   0.4123   0.0100
  -0.500   0.1871   0.00911   0.00166  -0.0182   0.4068   0.0178
  -0.250   0.2137   0.00903   0.00160  -0.0179   0.4015   0.0333
   0.000   0.2396   0.00884   0.00156  -0.0176   0.3966   0.0829
   0.250   0.2546   0.00765   0.00147  -0.0156   0.3923   0.4606
   0.500   0.2575   0.00637   0.00156  -0.0102   0.3887   0.8784
   0.750   0.2836   0.00645   0.00163  -0.0096   0.3844   0.8968
   1.000   0.3089   0.00656   0.00172  -0.0088   0.3796   0.9115
   1.250   0.3336   0.00669   0.00181  -0.0079   0.3750   0.9225
   1.500   0.3593   0.00679   0.00188  -0.0072   0.3712   0.9295
   1.750   0.3848   0.00688   0.00194  -0.0066   0.3668   0.9352
   2.000   0.4124   0.00694   0.00196  -0.0065   0.3622   0.9366
   2.250   0.4400   0.00702   0.00199  -0.0065   0.3581   0.9376
   2.500   0.4680   0.00706   0.00201  -0.0065   0.3542   0.9386
   2.750   0.4958   0.00713   0.00204  -0.0065   0.3498   0.9396
   3.000   0.5233   0.00721   0.00208  -0.0065   0.3455   0.9406
   3.250   0.5510   0.00728   0.00213  -0.0066   0.3417   0.9417
   3.500   0.5786   0.00734   0.00217  -0.0066   0.3377   0.9429
   3.750   0.6059   0.00742   0.00223  -0.0066   0.3332   0.9441
   4.000   0.6332   0.00752   0.00230  -0.0066   0.3290   0.9451
   4.250   0.6609   0.00759   0.00236  -0.0066   0.3251   0.9461
   4.500   0.6883   0.00767   0.00243  -0.0066   0.3207   0.9470
   4.750   0.7153   0.00778   0.00251  -0.0066   0.3156   0.9480
   5.000   0.7428   0.00786   0.00260  -0.0066   0.3115   0.9490
   5.250   0.7699   0.00795   0.00269  -0.0066   0.3065   0.9500
   5.500   0.7964   0.00808   0.00280  -0.0065   0.3010   0.9512
   5.750   0.8234   0.00817   0.00290  -0.0065   0.2961   0.9525
   6.000   0.8498   0.00830   0.00302  -0.0064   0.2902   0.9539
   6.250   0.8762   0.00843   0.00315  -0.0063   0.2843   0.9553
   6.500   0.9026   0.00856   0.00327  -0.0062   0.2777   0.9567
   6.750   0.9285   0.00872   0.00343  -0.0060   0.2708   0.9582
   7.000   0.9546   0.00887   0.00357  -0.0059   0.2642   0.9596
   7.250   0.9801   0.00905   0.00374  -0.0057   0.2572   0.9611
   7.500   1.0059   0.00922   0.00391  -0.0055   0.2489   0.9626
   7.750   1.0314   0.00942   0.00411  -0.0054   0.2400   0.9641
   8.000   1.0564   0.00966   0.00433  -0.0051   0.2303   0.9659
   8.250   1.0808   0.00995   0.00458  -0.0048   0.2180   0.9680
   8.500   1.1051   0.01022   0.00483  -0.0045   0.2069   0.9703
   8.750   1.1287   0.01050   0.00510  -0.0041   0.1959   0.9730
   9.000   1.1527   0.01083   0.00540  -0.0038   0.1844   0.9755
   9.250   1.1776   0.01126   0.00578  -0.0038   0.1694   0.9776
   9.500   1.2023   0.01170   0.00617  -0.0039   0.1554   0.9800
   9.750   1.2269   0.01214   0.00658  -0.0039   0.1432   0.9827
  10.000   1.2490   0.01272   0.00709  -0.0036   0.1269   0.9861
  10.250   1.2746   0.01330   0.00763  -0.0041   0.1129   0.9880
  10.500   1.2997   0.01390   0.00818  -0.0045   0.1003   0.9904
  10.750   1.3225   0.01462   0.00884  -0.0047   0.0845   0.9937
  11.000   1.3459   0.01528   0.00946  -0.0049   0.0741   0.9983
  11.250   1.3580   0.01593   0.01007  -0.0028   0.0646   1.0000
  11.500   1.3659   0.01653   0.01065   0.0001   0.0578   1.0000
  11.750   1.3677   0.01735   0.01143   0.0039   0.0473   1.0000
  12.000   1.3792   0.01788   0.01200   0.0059   0.0452   1.0000
  12.250   1.3848   0.01873   0.01286   0.0085   0.0397   1.0000
  12.500   1.3886   0.01977   0.01390   0.0110   0.0333   1.0000
  12.750   1.3920   0.02096   0.01510   0.0131   0.0290   1.0000
  13.000   1.3908   0.02261   0.01675   0.0151   0.0231   1.0000
  13.250   1.3879   0.02465   0.01880   0.0166   0.0178   1.0000
  13.500   1.4001   0.02569   0.01995   0.0170   0.0197   1.0000
  13.750   1.3983   0.02802   0.02231   0.0177   0.0161   1.0000
  14.000   1.3994   0.03027   0.02463   0.0180   0.0146   1.0000
  14.250   1.3996   0.03271   0.02714   0.0181   0.0136   1.0000
  14.500   1.3993   0.03529   0.02979   0.0180   0.0124   1.0000
  14.750   1.3969   0.03815   0.03273   0.0178   0.0112   1.0000
  15.000   1.3936   0.04116   0.03582   0.0174   0.0105   1.0000
  15.250   1.3813   0.04527   0.03997   0.0169   0.0078   1.0000
  15.500   1.3794   0.04825   0.04305   0.0164   0.0080   1.0000
  15.750   1.3756   0.05148   0.04636   0.0158   0.0080   1.0000
  16.000   1.3649   0.05565   0.05059   0.0149   0.0069   1.0000
  16.250   1.3600   0.05922   0.05426   0.0140   0.0068   1.0000
  16.500   1.3537   0.06307   0.05819   0.0129   0.0063   1.0000
  16.750   1.3444   0.06739   0.06258   0.0116   0.0054   1.0000
  17.000   1.3377   0.07146   0.06674   0.0103   0.0053   1.0000
  17.250   1.3289   0.07591   0.07126   0.0089   0.0046   1.0000
  17.500   1.3245   0.07984   0.07528   0.0075   0.0049   1.0000
  17.750   1.3176   0.08415   0.07967   0.0059   0.0045   1.0000
  18.000   1.3129   0.08823   0.08384   0.0044   0.0047   1.0000
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