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EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 420 AIRFOIL (e420-il)
Reynolds number: 500,000
Max Cl/Cd: 106.07 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e420-il-500000-n5.txt
Download as CSV file: xf-e420-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.4041   0.08724   0.08233  -0.1624   0.5827   0.0176
  -9.000   0.4121   0.08534   0.08043  -0.1627   0.5779   0.0176
  -8.750   0.4196   0.08345   0.07853  -0.1629   0.5731   0.0178
  -8.500   0.4270   0.08167   0.07672  -0.1629   0.5687   0.0179
  -8.250   0.4343   0.07979   0.07485  -0.1631   0.5651   0.0180
  -8.000   0.4415   0.07791   0.07298  -0.1632   0.5617   0.0181
  -7.750   0.4485   0.07612   0.07119  -0.1631   0.5580   0.0181
  -7.250   0.4449   0.06993   0.06501  -0.1628   0.5520   0.0135
  -7.000   0.4511   0.06857   0.06364  -0.1621   0.5485   0.0134
  -6.000   0.3883   0.02861   0.02325  -0.1995   0.5428   0.0108
  -5.750   0.4557   0.01926   0.01316  -0.2198   0.5393   0.0110
  -5.500   0.4893   0.01761   0.01125  -0.2228   0.5355   0.0113
  -5.250   0.5192   0.01674   0.01020  -0.2241   0.5317   0.0115
  -5.000   0.5483   0.01611   0.00941  -0.2249   0.5283   0.0118
  -4.750   0.5779   0.01555   0.00873  -0.2257   0.5254   0.0121
  -4.500   0.6069   0.01509   0.00814  -0.2262   0.5225   0.0125
  -4.250   0.6354   0.01469   0.00763  -0.2265   0.5195   0.0129
  -4.000   0.6634   0.01437   0.00719  -0.2267   0.5166   0.0133
  -3.750   0.6910   0.01412   0.00682  -0.2268   0.5138   0.0137
  -3.500   0.7187   0.01385   0.00644  -0.2269   0.5111   0.0142
  -3.250   0.7467   0.01364   0.00616  -0.2269   0.5089   0.0149
  -3.000   0.7746   0.01345   0.00591  -0.2270   0.5066   0.0156
  -2.750   0.8022   0.01329   0.00568  -0.2269   0.5041   0.0166
  -2.500   0.8294   0.01315   0.00549  -0.2268   0.5014   0.0184
  -2.250   0.8564   0.01304   0.00533  -0.2266   0.4988   0.0211
  -2.000   0.8831   0.01294   0.00519  -0.2264   0.4965   0.0250
  -1.750   0.9096   0.01288   0.00509  -0.2261   0.4942   0.0306
  -1.250   0.9630   0.01280   0.00500  -0.2257   0.4904   0.0475
  -1.000   0.9899   0.01276   0.00499  -0.2255   0.4887   0.0594
  -0.750   1.0165   0.01275   0.00499  -0.2253   0.4867   0.0707
  -0.500   1.0426   0.01276   0.00502  -0.2249   0.4845   0.0816
  -0.250   1.0685   0.01280   0.00506  -0.2245   0.4823   0.0930
   0.000   1.0941   0.01285   0.00511  -0.2241   0.4802   0.1035
   0.250   1.1197   0.01293   0.00518  -0.2237   0.4783   0.1136
   0.500   1.1450   0.01302   0.00526  -0.2232   0.4764   0.1232
   0.750   1.1702   0.01314   0.00535  -0.2227   0.4746   0.1324
   1.000   1.1959   0.01324   0.00546  -0.2223   0.4730   0.1425
   1.250   1.2216   0.01331   0.00556  -0.2220   0.4714   0.1518
   1.500   1.2470   0.01340   0.00567  -0.2215   0.4697   0.1615
   1.750   1.2721   0.01350   0.00579  -0.2210   0.4678   0.1708
   2.000   1.2969   0.01362   0.00591  -0.2205   0.4659   0.1801
   2.250   1.3217   0.01374   0.00605  -0.2200   0.4642   0.1886
   2.500   1.3461   0.01387   0.00619  -0.2194   0.4625   0.1977
   2.750   1.3702   0.01402   0.00633  -0.2188   0.4608   0.2056
   3.000   1.3941   0.01418   0.00649  -0.2182   0.4590   0.2149
   3.250   1.4176   0.01437   0.00666  -0.2175   0.4571   0.2230
   3.500   1.4417   0.01453   0.00686  -0.2169   0.4554   0.2324
   4.000   1.4897   0.01481   0.00722  -0.2158   0.4526   0.2520
   4.250   1.5133   0.01496   0.00742  -0.2152   0.4510   0.2624
   4.500   1.5366   0.01512   0.00763  -0.2145   0.4493   0.2751
   4.750   1.5595   0.01530   0.00784  -0.2138   0.4473   0.2889
   5.000   1.5820   0.01548   0.00807  -0.2130   0.4454   0.3048
   5.250   1.6044   0.01568   0.00831  -0.2123   0.4437   0.3238
   5.500   1.6265   0.01589   0.00857  -0.2115   0.4421   0.3508
   5.750   1.6484   0.01610   0.00886  -0.2107   0.4404   0.3914
   6.250   1.6908   0.01594   0.00952  -0.2089   0.4371   1.0000
   6.500   1.7124   0.01619   0.00980  -0.2081   0.4354   1.0000
   6.750   1.7336   0.01645   0.01008  -0.2072   0.4336   1.0000
   7.000   1.7540   0.01673   0.01039  -0.2062   0.4317   1.0000
   7.250   1.7739   0.01703   0.01070  -0.2051   0.4296   1.0000
   7.500   1.7933   0.01735   0.01105  -0.2039   0.4274   1.0000
   7.750   1.8120   0.01771   0.01140  -0.2027   0.4253   1.0000
   8.000   1.8298   0.01811   0.01179  -0.2013   0.4230   1.0000
   8.250   1.8484   0.01850   0.01220  -0.2002   0.4209   1.0000
   8.500   1.8669   0.01885   0.01263  -0.1990   0.4187   1.0000
   8.750   1.8845   0.01925   0.01308  -0.1977   0.4161   1.0000
   9.000   1.9013   0.01969   0.01356  -0.1963   0.4133   1.0000
   9.250   1.9168   0.02019   0.01408  -0.1948   0.4104   1.0000
   9.500   1.9312   0.02075   0.01465  -0.1931   0.4076   1.0000
   9.750   1.9456   0.02135   0.01527  -0.1915   0.4048   1.0000
  10.000   1.9613   0.02189   0.01589  -0.1901   0.4019   1.0000
  10.250   1.9758   0.02251   0.01657  -0.1887   0.3985   1.0000
  10.500   1.9886   0.02322   0.01732  -0.1870   0.3951   1.0000
  10.750   2.0000   0.02402   0.01815  -0.1852   0.3918   1.0000
  11.000   2.0110   0.02489   0.01906  -0.1834   0.3886   1.0000
  11.250   2.0241   0.02569   0.01994  -0.1820   0.3851   1.0000
  11.500   2.0346   0.02665   0.02096  -0.1804   0.3809   1.0000
  11.750   2.0423   0.02781   0.02215  -0.1784   0.3766   1.0000
  12.000   2.0500   0.02904   0.02342  -0.1766   0.3727   1.0000
  12.250   2.0594   0.03021   0.02467  -0.1751   0.3681   1.0000
  12.500   2.0653   0.03167   0.02618  -0.1733   0.3630   1.0000
  12.750   2.0673   0.03346   0.02799  -0.1713   0.3578   1.0000
  13.000   2.0737   0.03501   0.02963  -0.1698   0.3522   1.0000
  13.250   2.0736   0.03715   0.03180  -0.1679   0.3459   1.0000
  13.500   2.0740   0.03933   0.03403  -0.1661   0.3401   1.0000
  13.750   2.0722   0.04180   0.03655  -0.1644   0.3326   1.0000
  14.000   2.0668   0.04469   0.03947  -0.1626   0.3257   1.0000
  14.250   2.0616   0.04768   0.04252  -0.1610   0.3175   1.0000
  14.500   2.0527   0.05116   0.04603  -0.1594   0.3098   1.0000
  14.750   2.0417   0.05499   0.04991  -0.1578   0.3008   1.0000
  15.000   2.0310   0.05891   0.05387  -0.1565   0.2924   1.0000
  15.250   2.0128   0.06382   0.05880  -0.1552   0.2830   1.0000
  15.500   2.0015   0.06806   0.06309  -0.1542   0.2737   1.0000
  15.750   1.9846   0.07309   0.06814  -0.1533   0.2646   1.0000
  16.000   1.9677   0.07826   0.07334  -0.1526   0.2551   1.0000
  16.250   1.9551   0.08297   0.07809  -0.1521   0.2467   1.0000
  16.500   1.9372   0.08845   0.08358  -0.1517   0.2377   1.0000
  16.750   1.9290   0.09270   0.08786  -0.1516   0.2291   1.0000
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