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EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 420 AIRFOIL (e420-il)
Reynolds number: 100,000
Max Cl/Cd: 47.77 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e420-il-100000-n5.txt
Download as CSV file: xf-e420-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 420 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.3267   0.10427   0.09789  -0.1455   0.7527   0.0475
  -9.750   0.3387   0.10208   0.09562  -0.1479   0.7421   0.0483
  -9.500   0.3493   0.10012   0.09359  -0.1499   0.7320   0.0486
  -9.000   0.3728   0.09553   0.08890  -0.1524   0.7138   0.0492
  -8.750   0.3880   0.09306   0.08633  -0.1535   0.7060   0.0501
  -8.500   0.3971   0.09123   0.08450  -0.1538   0.6975   0.0508
  -8.250   0.4071   0.08932   0.08253  -0.1545   0.6899   0.0517
  -8.000   0.4161   0.08750   0.08067  -0.1551   0.6832   0.0526
  -7.750   0.4224   0.08589   0.07906  -0.1554   0.6761   0.0534
  -7.500   0.4269   0.08435   0.07749  -0.1560   0.6699   0.0541
  -7.250   0.4322   0.08277   0.07587  -0.1566   0.6647   0.0544
  -7.000   0.4345   0.08129   0.07444  -0.1563   0.6585   0.0545
  -6.750   0.4383   0.07971   0.07287  -0.1561   0.6532   0.0545
  -6.500   0.4499   0.07742   0.07053  -0.1559   0.6485   0.0549
  -6.250   0.4475   0.07640   0.06952  -0.1554   0.6440   0.0545
  -6.000   0.4622   0.07413   0.06727  -0.1543   0.6386   0.0556
  -5.750   0.4677   0.07275   0.06590  -0.1531   0.6337   0.0571
  -5.500   0.4677   0.07168   0.06483  -0.1532   0.6294   0.0601
  -5.000   0.4767   0.06649   0.05961  -0.1542   0.6214   0.0430
  -4.500   0.4920   0.06174   0.05486  -0.1570   0.6132   0.0385
  -4.250   0.5063   0.05976   0.05285  -0.1582   0.6097   0.0378
  -4.000   0.5248   0.05717   0.05018  -0.1613   0.6068   0.0370
  -3.750   0.5406   0.05457   0.04759  -0.1641   0.6031   0.0364
  -3.500   0.5612   0.05145   0.04445  -0.1683   0.5993   0.0357
  -3.250   0.5915   0.04747   0.04038  -0.1751   0.5956   0.0355
  -3.000   0.6366   0.04225   0.03495  -0.1857   0.5922   0.0359
  -2.750   0.7534   0.02762   0.01863  -0.2181   0.5893   0.0428
  -2.500   0.7902   0.02647   0.01711  -0.2207   0.5864   0.0465
  -2.250   0.8171   0.02592   0.01641  -0.2212   0.5826   0.0521
  -2.000   0.8455   0.02543   0.01574  -0.2217   0.5791   0.0590
  -1.750   0.8745   0.02511   0.01525  -0.2223   0.5758   0.0686
  -1.500   0.9031   0.02504   0.01511  -0.2227   0.5729   0.0796
  -1.250   0.9334   0.02491   0.01475  -0.2233   0.5702   0.0940
  -1.000   0.9638   0.02495   0.01470  -0.2238   0.5678   0.1071
  -0.750   0.9878   0.02509   0.01480  -0.2233   0.5646   0.1194
  -0.500   1.0106   0.02525   0.01491  -0.2225   0.5612   0.1318
  -0.250   1.0342   0.02547   0.01516  -0.2219   0.5580   0.1428
   0.000   1.0597   0.02564   0.01527  -0.2216   0.5553   0.1543
   0.250   1.0868   0.02576   0.01528  -0.2215   0.5529   0.1672
   0.500   1.1151   0.02592   0.01531  -0.2217   0.5507   0.1807
   0.750   1.1446   0.02606   0.01539  -0.2221   0.5487   0.1930
   1.000   1.1667   0.02635   0.01564  -0.2212   0.5460   0.2049
   1.250   1.1846   0.02675   0.01610  -0.2197   0.5427   0.2155
   1.500   1.2050   0.02708   0.01644  -0.2185   0.5397   0.2267
   1.750   1.2279   0.02741   0.01672  -0.2179   0.5372   0.2396
   2.000   1.2526   0.02768   0.01700  -0.2175   0.5349   0.2513
   2.250   1.2786   0.02793   0.01718  -0.2173   0.5328   0.2647
   2.500   1.3066   0.02815   0.01729  -0.2174   0.5309   0.2794
   2.750   1.3367   0.02833   0.01741  -0.2180   0.5290   0.2945
   3.000   1.3463   0.02902   0.01824  -0.2151   0.5259   0.3053
   3.250   1.3581   0.02969   0.01900  -0.2126   0.5228   0.3187
   3.500   1.3733   0.03029   0.01967  -0.2108   0.5202   0.3334
   3.750   1.3911   0.03081   0.02024  -0.2094   0.5178   0.3510
   4.000   1.4126   0.03120   0.02068  -0.2086   0.5155   0.3740
   4.250   1.4386   0.03145   0.02099  -0.2086   0.5135   0.4083
   4.500   1.4692   0.03137   0.02126  -0.2094   0.5117   0.5566
   4.750   1.4933   0.03126   0.02136  -0.2086   0.5101   1.0000
   5.000   1.4741   0.03294   0.02325  -0.2015   0.5063   1.0000
   5.250   1.4653   0.03452   0.02493  -0.1962   0.5028   1.0000
   5.500   1.4682   0.03577   0.02621  -0.1929   0.4997   1.0000
   5.750   1.4823   0.03659   0.02699  -0.1912   0.4972   1.0000
   6.000   1.5051   0.03706   0.02740  -0.1907   0.4951   1.0000
   6.250   1.5345   0.03730   0.02757  -0.1911   0.4935   1.0000
   6.500   1.5672   0.03751   0.02768  -0.1920   0.4922   1.0000
   6.750   1.4022   0.04905   0.03992  -0.1718   0.4785   1.0000
   7.000   1.4279   0.04925   0.04008  -0.1716   0.4769   1.0000
   7.250   1.4574   0.04920   0.03995  -0.1716   0.4757   1.0000
   7.500   1.4894   0.04899   0.03968  -0.1720   0.4746   1.0000
   7.750   1.5255   0.04852   0.03914  -0.1727   0.4738   1.0000
  10.250   1.2467   0.11197   0.10373  -0.1571   0.3815   1.0000
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