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EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 858 AIRFOIL (e858-il)
Reynolds number: 50,000
Max Cl/Cd: 3.03 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e858-il-50000.txt
Download as CSV file: xf-e858-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 858 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2499   0.13238   0.12691  -0.0326   0.9831   0.2501
  -9.750  -0.5796   0.08423   0.07891  -0.0550   0.9896   0.1497
  -9.500  -0.5888   0.07814   0.07272  -0.0610   0.9777   0.1528
  -9.250  -0.6867   0.06758   0.06155  -0.0655   0.9634   0.1442
  -9.000  -0.7033   0.06199   0.05538  -0.0681   0.9499   0.1469
  -8.750  -0.6753   0.05971   0.05312  -0.0704   0.9365   0.1566
  -8.500  -0.6613   0.05652   0.04968  -0.0722   0.9235   0.1658
  -8.250  -0.6404   0.05397   0.04693  -0.0739   0.9110   0.1784
  -8.000  -0.5994   0.05264   0.04577  -0.0766   0.8994   0.1977
  -7.750  -0.5796   0.05157   0.04478  -0.0763   0.8851   0.2144
  -7.500  -0.5580   0.05098   0.04429  -0.0759   0.8718   0.2335
  -7.250  -0.5166   0.05138   0.04489  -0.0770   0.8602   0.2605
  -7.000  -0.4759   0.05351   0.04725  -0.0760   0.8463   0.2863
  -6.750  -0.4560   0.05470   0.04847  -0.0738   0.8325   0.3074
  -6.500  -0.2129   0.07111   0.06489  -0.0749   0.8231   0.3619
  -6.250  -0.2948   0.06703   0.06091  -0.0695   0.8069   0.3627
  -6.000  -0.1673   0.06975   0.06328  -0.0738   0.8017   0.4049
  -5.750  -0.2404   0.06844   0.06209  -0.0661   0.7847   0.4048
  -5.500  -0.1659   0.07012   0.06356  -0.0662   0.7760   0.4330
  -5.250  -0.1739   0.07018   0.06359  -0.0621   0.7636   0.4466
  -5.000   0.1311   0.06773   0.06026  -0.0872   0.7625   0.5332
  -4.750  -0.2131   0.06888   0.06224  -0.0546   0.7428   0.4717
  -4.500   0.0067   0.06867   0.06144  -0.0672   0.7390   0.5296
  -4.250  -0.2236   0.06890   0.06216  -0.0476   0.7240   0.4990
  -4.000  -0.2036   0.06802   0.06110  -0.0473   0.7171   0.5202
  -3.750  -0.1779   0.07027   0.06336  -0.0423   0.7085   0.5321
  -3.500  -0.2210   0.07005   0.06315  -0.0379   0.7006   0.5391
  -3.250  -0.1805   0.06973   0.06268  -0.0372   0.6939   0.5590
  -3.000  -0.2028   0.06929   0.06217  -0.0348   0.6878   0.5691
  -2.750  -0.2291   0.07065   0.06360  -0.0294   0.6818   0.5739
  -2.500  -0.2339   0.07068   0.06354  -0.0280   0.6773   0.5857
  -2.250  -0.2094   0.07062   0.06339  -0.0265   0.6719   0.5996
  -2.000  -0.1974   0.07002   0.06259  -0.0277   0.6673   0.6135
  -1.750  -0.2200   0.07136   0.06400  -0.0232   0.6645   0.6179
  -1.500  -0.2282   0.07225   0.06487  -0.0208   0.6629   0.6255
  -1.250  -0.2268   0.07266   0.06514  -0.0220   0.6634   0.6357
  -1.000  -0.2271   0.07364   0.06614  -0.0192   0.6646   0.6424
  -0.750  -0.2364   0.07487   0.06737  -0.0181   0.6731   0.6490
  -0.500  -0.2064   0.07528   0.06759  -0.0204   0.6699   0.6604
   0.000  -0.3271   0.07911   0.07179  -0.0139   0.7917   0.6588
   0.250  -0.3043   0.08012   0.07274  -0.0136   0.7835   0.6678
   0.500  -0.2760   0.08190   0.07433  -0.0165   0.7789   0.6783
   0.750  -0.2758   0.08077   0.07315  -0.0143   0.7669   0.6836
   1.000  -0.2486   0.08223   0.07451  -0.0155   0.7609   0.6921
   1.250  -0.2216   0.08421   0.07630  -0.0183   0.7570   0.7008
   1.500  -0.2226   0.08303   0.07509  -0.0161   0.7448   0.7055
   1.750  -0.1911   0.08494   0.07689  -0.0179   0.7382   0.7135
   2.000  -0.1816   0.08554   0.07739  -0.0180   0.7317   0.7201
   2.250  -0.1657   0.08591   0.07766  -0.0185   0.7209   0.7267
   2.500  -0.1351   0.08808   0.07975  -0.0201   0.7156   0.7348
   2.750  -0.1238   0.08916   0.08074  -0.0204   0.7109   0.7415
   3.000  -0.1144   0.08911   0.08063  -0.0201   0.6991   0.7483
   3.250  -0.0822   0.09151   0.08293  -0.0219   0.6934   0.7576
   3.500  -0.0741   0.09239   0.08373  -0.0219   0.6874   0.7647
   3.750  -0.0617   0.09281   0.08411  -0.0218   0.6768   0.7719
   4.000  -0.0311   0.09523   0.08644  -0.0237   0.6715   0.7825
   4.250   0.0039   0.09916   0.09027  -0.0263   0.6685   0.7942
   4.500  -0.0131   0.09680   0.08795  -0.0232   0.6567   0.8003
   4.750   0.0167   0.09909   0.09017  -0.0251   0.6501   0.8129
   5.000   0.0585   0.10364   0.09467  -0.0282   0.6468   0.8296
   5.250   0.0372   0.10119   0.09229  -0.0251   0.6363   0.8369
   5.500   0.0611   0.10301   0.09414  -0.0263   0.6297   0.8555
   5.750   0.0994   0.10659   0.09781  -0.0293   0.6258   0.8818
   6.000   0.0990   0.10658   0.09793  -0.0297   0.6181   0.9036
   6.250   0.1342   0.10846   0.09990  -0.0349   0.6082   1.0000
   6.500   0.1803   0.11313   0.10437  -0.0409   0.6039   1.0000
   6.750   0.1822   0.11396   0.10511  -0.0421   0.5984   1.0000
   7.000   0.1982   0.11534   0.10637  -0.0444   0.5892   1.0000
   7.250   0.2333   0.11891   0.10975  -0.0483   0.5838   1.0000
   7.500   0.2801   0.12511   0.11573  -0.0531   0.5808   1.0000
   7.750   0.2557   0.12242   0.11301  -0.0510   0.5710   1.0000
   8.000   0.2786   0.12495   0.11540  -0.0528   0.5647   1.0000
   8.250   0.3104   0.12899   0.11928  -0.0551   0.5609   1.0000
   8.500   0.3376   0.13378   0.12393  -0.0572   0.5583   1.0000
   8.750   0.3183   0.13121   0.12135  -0.0554   0.5480   1.0000
   9.000   0.3409   0.13394   0.12398  -0.0566   0.5421   1.0000
   9.250   0.3732   0.13861   0.12854  -0.0585   0.5387   1.0000
   9.500   0.3745   0.14003   0.12991  -0.0585   0.5354   1.0000
   9.750   0.3730   0.13981   0.12967  -0.0582   0.5265   1.0000
  10.000   0.3941   0.14255   0.13234  -0.0591   0.5209   1.0000
  10.250   0.4250   0.14733   0.13704  -0.0607   0.5176   1.0000
  10.500   0.4232   0.14825   0.13793  -0.0607   0.5138   1.0000
  10.750   0.4242   0.14838   0.13805  -0.0606   0.5057   1.0000
  11.000   0.4434   0.15105   0.14068  -0.0615   0.5003   1.0000
  11.250   0.4722   0.15571   0.14529  -0.0628   0.4968   1.0000
  11.500   0.4789   0.15802   0.14758  -0.0633   0.4939   1.0000
  11.750   0.4730   0.15698   0.14654  -0.0631   0.4856   1.0000
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