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EPPLER 420 AIRFOIL (e420-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 420 AIRFOIL (e420-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.13 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e420-il-1000000-n5.txt
Download as CSV file: xf-e420-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000   0.4471   0.07296   0.06865  -0.1687   0.5277   0.0106
  -7.500   0.4649   0.07023   0.06595  -0.1686   0.5221   0.0117
  -7.000   0.2965   0.03254   0.02803  -0.1940   0.5253   0.0082
  -6.750   0.3650   0.01917   0.01396  -0.2226   0.5223   0.0082
  -6.500   0.4007   0.01615   0.01064  -0.2274   0.5186   0.0083
  -6.250   0.4306   0.01513   0.00945  -0.2289   0.5147   0.0083
  -5.750   0.4894   0.01363   0.00765  -0.2307   0.5085   0.0085
  -5.500   0.5190   0.01297   0.00685  -0.2315   0.5061   0.0087
  -5.250   0.5475   0.01256   0.00634  -0.2318   0.5036   0.0089
  -5.000   0.5755   0.01224   0.00595  -0.2319   0.5008   0.0092
  -4.750   0.6031   0.01200   0.00563  -0.2319   0.4981   0.0094
  -4.500   0.6304   0.01180   0.00535  -0.2318   0.4953   0.0097
  -4.000   0.6852   0.01145   0.00488  -0.2316   0.4905   0.0103
  -3.750   0.7129   0.01129   0.00467  -0.2315   0.4885   0.0106
  -3.500   0.7404   0.01117   0.00449  -0.2314   0.4862   0.0108
  -3.250   0.7679   0.01102   0.00430  -0.2313   0.4839   0.0113
  -3.000   0.7950   0.01092   0.00415  -0.2311   0.4817   0.0118
  -2.750   0.8218   0.01084   0.00404  -0.2308   0.4795   0.0125
  -2.500   0.8483   0.01080   0.00395  -0.2305   0.4772   0.0133
  -2.250   0.8748   0.01075   0.00386  -0.2301   0.4749   0.0146
  -2.000   0.9016   0.01071   0.00380  -0.2299   0.4731   0.0164
  -1.750   0.9288   0.01064   0.00373  -0.2297   0.4718   0.0192
  -1.500   0.9560   0.01059   0.00368  -0.2295   0.4701   0.0234
  -1.250   0.9830   0.01054   0.00365  -0.2293   0.4683   0.0313
  -1.000   1.0098   0.01052   0.00364  -0.2291   0.4663   0.0404
  -0.750   1.0363   0.01052   0.00365  -0.2288   0.4645   0.0499
  -0.500   1.0627   0.01052   0.00368  -0.2285   0.4627   0.0614
  -0.250   1.0888   0.01055   0.00373  -0.2282   0.4609   0.0730
   0.250   1.1399   0.01067   0.00386  -0.2273   0.4567   0.0959
   0.500   1.1659   0.01072   0.00392  -0.2269   0.4552   0.1053
   0.750   1.1922   0.01075   0.00399  -0.2266   0.4540   0.1155
   1.000   1.2182   0.01080   0.00406  -0.2263   0.4526   0.1243
   1.250   1.2440   0.01087   0.00414  -0.2259   0.4512   0.1321
   1.500   1.2696   0.01093   0.00423  -0.2255   0.4497   0.1419
   1.750   1.2949   0.01102   0.00432  -0.2250   0.4482   0.1503
   2.000   1.3200   0.01111   0.00443  -0.2245   0.4464   0.1602
   2.250   1.3447   0.01121   0.00454  -0.2240   0.4445   0.1679
   2.500   1.3690   0.01133   0.00466  -0.2234   0.4426   0.1769
   2.750   1.3930   0.01147   0.00479  -0.2227   0.4407   0.1835
   3.000   1.4166   0.01161   0.00495  -0.2220   0.4388   0.1922
   3.250   1.4414   0.01171   0.00507  -0.2215   0.4379   0.2000
   3.500   1.4662   0.01181   0.00520  -0.2210   0.4367   0.2079
   3.750   1.4908   0.01191   0.00534  -0.2206   0.4353   0.2164
   4.000   1.5151   0.01203   0.00547  -0.2200   0.4338   0.2229
   4.250   1.5391   0.01215   0.00563  -0.2194   0.4321   0.2332
   4.500   1.5629   0.01229   0.00579  -0.2188   0.4306   0.2409
   4.750   1.5864   0.01243   0.00596  -0.2182   0.4290   0.2526
   5.000   1.6092   0.01260   0.00615  -0.2174   0.4272   0.2621
   5.250   1.6312   0.01278   0.00636  -0.2166   0.4252   0.2754
   5.500   1.6524   0.01300   0.00660  -0.2156   0.4231   0.2889
   5.750   1.6745   0.01319   0.00683  -0.2147   0.4215   0.3042
   6.000   1.6982   0.01332   0.00703  -0.2142   0.4203   0.3273
   6.250   1.7215   0.01346   0.00724  -0.2137   0.4188   0.3545
   6.500   1.7446   0.01360   0.00748  -0.2131   0.4169   0.4010
   6.750   1.7665   0.01317   0.00789  -0.2125   0.4148   1.0000
   7.000   1.7874   0.01341   0.00814  -0.2115   0.4125   1.0000
   7.250   1.8075   0.01369   0.00842  -0.2104   0.4101   1.0000
   7.500   1.8266   0.01401   0.00873  -0.2092   0.4074   1.0000
   7.750   1.8462   0.01432   0.00904  -0.2080   0.4049   1.0000
   8.000   1.8676   0.01456   0.00931  -0.2073   0.4028   1.0000
   8.250   1.8880   0.01483   0.00961  -0.2063   0.4001   1.0000
   8.500   1.9074   0.01515   0.00994  -0.2052   0.3969   1.0000
   8.750   1.9252   0.01554   0.01033  -0.2039   0.3936   1.0000
   9.000   1.9408   0.01601   0.01081  -0.2022   0.3903   1.0000
   9.250   1.9598   0.01637   0.01120  -0.2012   0.3877   1.0000
   9.500   1.9785   0.01674   0.01160  -0.2001   0.3843   1.0000
   9.750   1.9953   0.01720   0.01208  -0.1987   0.3807   1.0000
  10.000   2.0102   0.01776   0.01264  -0.1972   0.3769   1.0000
  10.250   2.0235   0.01840   0.01329  -0.1954   0.3731   1.0000
  10.500   2.0406   0.01889   0.01382  -0.1942   0.3695   1.0000
  10.750   2.0549   0.01952   0.01448  -0.1927   0.3649   1.0000
  11.000   2.0652   0.02039   0.01535  -0.1907   0.3597   1.0000
  11.250   2.0782   0.02113   0.01613  -0.1891   0.3555   1.0000
  11.500   2.0897   0.02200   0.01701  -0.1874   0.3493   1.0000
  11.750   2.0951   0.02326   0.01826  -0.1850   0.3431   1.0000
  12.000   2.1064   0.02421   0.01925  -0.1834   0.3371   1.0000
  12.250   2.1115   0.02560   0.02065  -0.1812   0.3302   1.0000
  12.500   2.1161   0.02708   0.02215  -0.1791   0.3231   1.0000
  12.750   2.1177   0.02886   0.02394  -0.1768   0.3150   1.0000
  13.000   2.1189   0.03075   0.02584  -0.1746   0.3068   1.0000
  13.250   2.1139   0.03324   0.02833  -0.1721   0.2979   1.0000
  13.500   2.1127   0.03552   0.03063  -0.1701   0.2888   1.0000
  13.750   2.1050   0.03848   0.03359  -0.1678   0.2802   1.0000
  14.000   2.0954   0.04176   0.03690  -0.1656   0.2703   1.0000
  14.250   2.0868   0.04508   0.04024  -0.1636   0.2619   1.0000
  14.500   2.0706   0.04933   0.04450  -0.1616   0.2525   1.0000
  14.750   2.0595   0.05319   0.04840  -0.1600   0.2435   1.0000
  15.000   2.0436   0.05773   0.05296  -0.1584   0.2351   1.0000
  15.250   2.0299   0.06215   0.05741  -0.1572   0.2270   1.0000
  15.500   2.0151   0.06683   0.06213  -0.1561   0.2190   1.0000
  15.750   1.9989   0.07182   0.06714  -0.1552   0.2109   1.0000
  16.000   1.9889   0.07610   0.07146  -0.1545   0.2038   1.0000
  16.250   1.9728   0.08128   0.07667  -0.1540   0.1962   1.0000
  16.500   1.9629   0.08575   0.08117  -0.1536   0.1897   1.0000
  16.750   1.9495   0.09072   0.08617  -0.1534   0.1823   1.0000
  17.000   1.9424   0.09489   0.09037  -0.1533   0.1759   1.0000
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