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EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E851 AIRFOIL (e851-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.68 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e851-il-1000000-n5.txt
Download as CSV file: xf-e851-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E851 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4630   0.11370   0.11201  -0.0297   1.0000   0.0030
 -10.500  -0.4675   0.10880   0.10712  -0.0309   1.0000   0.0031
 -10.250  -0.4700   0.10466   0.10301  -0.0318   1.0000   0.0032
 -10.000  -0.4697   0.10030   0.09867  -0.0337   0.9998   0.0033
  -9.750  -0.4629   0.09533   0.09370  -0.0372   0.9991   0.0032
  -9.500  -0.4582   0.09014   0.08851  -0.0413   0.9982   0.0033
  -9.250  -0.4531   0.08494   0.08332  -0.0457   0.9970   0.0034
  -9.000  -0.3622   0.06452   0.06299  -0.0587   0.9918   0.0035
  -8.750  -0.3666   0.05768   0.05616  -0.0628   0.9894   0.0034
  -8.500  -0.3689   0.05092   0.04941  -0.0685   0.9865   0.0036
  -8.250  -0.3833   0.03946   0.03784  -0.0816   0.9823   0.0034
  -8.000  -0.3940   0.03423   0.03246  -0.0876   0.9711   0.0034
  -7.750  -0.3939   0.02848   0.02651  -0.0910   0.9624   0.0034
  -7.500  -0.3822   0.02297   0.02073  -0.0947   0.9572   0.0035
  -7.250  -0.3683   0.01809   0.01554  -0.0968   0.9501   0.0035
  -7.000  -0.3455   0.01483   0.01200  -0.0980   0.9448   0.0031
  -6.750  -0.3229   0.01306   0.01007  -0.0991   0.9385   0.0026
  -6.500  -0.3232   0.02072   0.01709  -0.1015   0.9414   0.0023
  -6.250  -0.2991   0.01667   0.01252  -0.1017   0.9342   0.0019
  -6.000  -0.2729   0.01378   0.00923  -0.1017   0.9282   0.0017
  -5.750  -0.2479   0.01186   0.00701  -0.1013   0.9212   0.0015
  -5.500  -0.2224   0.01048   0.00539  -0.1009   0.9151   0.0014
  -5.250  -0.1970   0.00956   0.00429  -0.1006   0.9090   0.0014
  -5.000  -0.1700   0.00894   0.00346  -0.1006   0.9040   0.0013
  -4.750  -0.1435   0.00851   0.00291  -0.1004   0.8987   0.0014
  -4.500  -0.1161   0.00820   0.00250  -0.1005   0.8938   0.0014
  -4.250  -0.0885   0.00796   0.00216  -0.1005   0.8897   0.0015
  -4.000  -0.0611   0.00776   0.00191  -0.1005   0.8853   0.0018
  -3.750  -0.0335   0.00762   0.00172  -0.1006   0.8811   0.0026
  -3.500  -0.0060   0.00738   0.00153  -0.1007   0.8774   0.0168
  -3.250   0.0212   0.00715   0.00138  -0.1008   0.8735   0.0401
  -3.000   0.0485   0.00692   0.00122  -0.1009   0.8697   0.0722
  -2.750   0.0730   0.00581   0.00092  -0.1012   0.8658   0.3126
  -2.500   0.0997   0.00545   0.00085  -0.1014   0.8623   0.4054
  -2.250   0.1275   0.00535   0.00081  -0.1015   0.8587   0.4359
  -2.000   0.1554   0.00529   0.00078  -0.1017   0.8553   0.4589
  -1.750   0.1833   0.00523   0.00077  -0.1018   0.8522   0.4834
  -1.500   0.2112   0.00519   0.00074  -0.1019   0.8489   0.5036
  -1.250   0.2391   0.00515   0.00074  -0.1020   0.8452   0.5191
  -1.000   0.2671   0.00514   0.00073  -0.1021   0.8413   0.5300
  -0.750   0.2949   0.00513   0.00072  -0.1022   0.8369   0.5378
  -0.500   0.3226   0.00512   0.00072  -0.1022   0.8308   0.5447
  -0.250   0.3501   0.00513   0.00073  -0.1022   0.8243   0.5516
   0.000   0.3774   0.00513   0.00074  -0.1021   0.8163   0.5585
   0.250   0.4046   0.00514   0.00075  -0.1020   0.8073   0.5656
   0.500   0.4315   0.00516   0.00076  -0.1019   0.7968   0.5727
   0.750   0.4583   0.00518   0.00079  -0.1017   0.7848   0.5803
   1.000   0.4844   0.00522   0.00081  -0.1013   0.7661   0.5878
   1.250   0.5090   0.00532   0.00087  -0.1006   0.7351   0.5960
   1.500   0.5307   0.00557   0.00093  -0.0993   0.6782   0.6039
   1.750   0.5494   0.00604   0.00108  -0.0974   0.5917   0.6121
   2.000   0.5680   0.00663   0.00131  -0.0957   0.4970   0.6213
   2.250   0.5877   0.00720   0.00155  -0.0943   0.4048   0.6308
   2.500   0.6033   0.00815   0.00190  -0.0922   0.2559   0.6405
   2.750   0.6240   0.00874   0.00221  -0.0911   0.1697   0.6513
   3.000   0.6434   0.00947   0.00255  -0.0897   0.0710   0.6625
   3.250   0.6655   0.00999   0.00285  -0.0888   0.0197   0.6749
   3.500   0.6908   0.01018   0.00306  -0.0884   0.0126   0.6886
   3.750   0.7148   0.01051   0.00336  -0.0877   0.0018   0.7033
   4.000   0.7401   0.01069   0.00362  -0.0873   0.0013   0.7197
   4.250   0.7650   0.01092   0.00394  -0.0868   0.0010   0.7375
   4.500   0.7894   0.01120   0.00432  -0.0862   0.0009   0.7570
   4.750   0.8133   0.01151   0.00477  -0.0854   0.0008   0.7796
   5.000   0.8363   0.01189   0.00530  -0.0844   0.0008   0.8054
   5.250   0.8580   0.01236   0.00602  -0.0832   0.0008   0.8370
   5.500   0.8776   0.01286   0.00674  -0.0814   0.0008   0.8816
   5.750   0.8965   0.01348   0.00765  -0.0793   0.0008   1.0000
   6.000   0.9168   0.01453   0.00885  -0.0778   0.0008   1.0000
   6.250   0.9366   0.01601   0.01053  -0.0761   0.0008   1.0000
   6.500   0.9572   0.01817   0.01295  -0.0744   0.0009   1.0000
   6.750   0.9781   0.02125   0.01640  -0.0726   0.0010   1.0000
   7.000   0.9948   0.02535   0.02098  -0.0699   0.0012   1.0000
   7.250   1.0049   0.03007   0.02618  -0.0663   0.0014   1.0000
   7.500   1.0081   0.03543   0.03202  -0.0619   0.0015   1.0000
  12.000   0.8469   0.13389   0.13247  -0.0656   0.0022   1.0000
  12.250   0.8454   0.14022   0.13878  -0.0686   0.0023   1.0000
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