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EPPLER 421 AIRFOIL (e421-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 421 AIRFOIL (e421-il)
Reynolds number: 200,000
Max Cl/Cd: 74.79 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e421-il-200000-n5.txt
Download as CSV file: xf-e421-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 421 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.1932   0.09829   0.09295  -0.1240   0.6836   0.0298
  -9.750   0.1986   0.09441   0.08900  -0.1243   0.6743   0.0222
  -9.250   0.2047   0.08805   0.08256  -0.1260   0.6575   0.0192
  -8.750   0.2213   0.08405   0.07849  -0.1265   0.6412   0.0187
  -8.500   0.2257   0.08138   0.07580  -0.1272   0.6342   0.0187
  -8.250   0.2318   0.07912   0.07350  -0.1276   0.6276   0.0184
  -8.000   0.2366   0.07660   0.07098  -0.1282   0.6213   0.0183
  -7.750   0.2399   0.07393   0.06831  -0.1287   0.6155   0.0182
  -7.250   0.2431   0.06835   0.06273  -0.1297   0.6051   0.0182
  -7.000   0.2339   0.06432   0.05874  -0.1303   0.6007   0.0190
  -6.500   0.1744   0.02633   0.01964  -0.1722   0.5990   0.0190
  -6.250   0.1995   0.02432   0.01729  -0.1741   0.5934   0.0195
  -6.000   0.2252   0.02310   0.01587  -0.1750   0.5879   0.0201
  -5.750   0.2511   0.02193   0.01448  -0.1756   0.5820   0.0207
  -5.500   0.2771   0.02089   0.01315  -0.1760   0.5765   0.0217
  -5.250   0.3036   0.02002   0.01202  -0.1762   0.5719   0.0227
  -5.000   0.3303   0.01939   0.01131  -0.1764   0.5669   0.0238
  -4.750   0.3573   0.01879   0.01053  -0.1765   0.5621   0.0254
  -4.500   0.3842   0.01832   0.00992  -0.1765   0.5578   0.0277
  -4.000   0.4388   0.01749   0.00884  -0.1765   0.5497   0.0349
  -3.750   0.4661   0.01712   0.00838  -0.1765   0.5453   0.0398
  -3.500   0.4932   0.01685   0.00802  -0.1764   0.5411   0.0464
  -3.250   0.5205   0.01665   0.00771  -0.1762   0.5374   0.0545
  -3.000   0.5479   0.01649   0.00746  -0.1761   0.5341   0.0636
  -2.750   0.5753   0.01635   0.00731  -0.1760   0.5305   0.0731
  -2.500   0.6026   0.01625   0.00717  -0.1759   0.5270   0.0828
  -2.250   0.6298   0.01619   0.00705  -0.1757   0.5237   0.0926
  -2.000   0.6570   0.01618   0.00695  -0.1755   0.5205   0.1025
  -1.750   0.6845   0.01619   0.00689  -0.1753   0.5176   0.1123
  -1.500   0.7114   0.01617   0.00687  -0.1751   0.5144   0.1218
  -1.250   0.7384   0.01617   0.00683  -0.1748   0.5110   0.1317
  -1.000   0.7653   0.01621   0.00685  -0.1746   0.5080   0.1415
  -0.750   0.7923   0.01624   0.00685  -0.1744   0.5053   0.1510
  -0.500   0.8194   0.01632   0.00684  -0.1741   0.5027   0.1612
  -0.250   0.8467   0.01640   0.00688  -0.1740   0.5003   0.1705
   0.000   0.8736   0.01649   0.00691  -0.1737   0.4977   0.1803
   0.250   0.8997   0.01653   0.00701  -0.1734   0.4947   0.1895
   0.500   0.9261   0.01662   0.00706  -0.1730   0.4918   0.1992
   0.750   0.9524   0.01669   0.00715  -0.1728   0.4892   0.2085
   1.000   0.9790   0.01680   0.00721  -0.1725   0.4868   0.2185
   1.250   1.0056   0.01689   0.00731  -0.1723   0.4846   0.2283
   1.500   1.0327   0.01703   0.00738  -0.1721   0.4824   0.2388
   1.750   1.0588   0.01714   0.00753  -0.1718   0.4801   0.2496
   2.000   1.0841   0.01725   0.00769  -0.1714   0.4775   0.2609
   2.250   1.1095   0.01737   0.00786  -0.1709   0.4749   0.2738
   2.500   1.1350   0.01750   0.00803  -0.1706   0.4726   0.2875
   2.750   1.1607   0.01763   0.00820  -0.1702   0.4704   0.3034
   3.000   1.1863   0.01776   0.00837  -0.1699   0.4682   0.3230
   3.250   1.2124   0.01791   0.00853  -0.1697   0.4660   0.3472
   3.500   1.2392   0.01806   0.00871  -0.1696   0.4640   0.3809
   3.750   1.2626   0.01815   0.00899  -0.1689   0.4617   0.4369
   4.250   1.3096   0.01783   0.00951  -0.1673   0.4572   1.0000
   4.500   1.3337   0.01809   0.00976  -0.1668   0.4549   1.0000
   4.750   1.3579   0.01834   0.00998  -0.1662   0.4527   1.0000
   5.000   1.3824   0.01860   0.01019  -0.1657   0.4505   1.0000
   5.250   1.4078   0.01887   0.01040  -0.1654   0.4485   1.0000
   5.500   1.4344   0.01918   0.01065  -0.1654   0.4467   1.0000
   5.750   1.4556   0.01950   0.01103  -0.1643   0.4446   1.0000
   6.000   1.4766   0.01982   0.01141  -0.1633   0.4422   1.0000
   6.250   1.4977   0.02014   0.01176  -0.1623   0.4397   1.0000
   6.500   1.5193   0.02045   0.01210  -0.1614   0.4373   1.0000
   6.750   1.5413   0.02076   0.01242  -0.1606   0.4351   1.0000
   7.000   1.5639   0.02106   0.01273  -0.1598   0.4332   1.0000
   7.250   1.5881   0.02137   0.01301  -0.1594   0.4312   1.0000
   7.500   1.6111   0.02171   0.01335  -0.1588   0.4291   1.0000
   7.750   1.6256   0.02213   0.01388  -0.1568   0.4265   1.0000
   8.000   1.6407   0.02253   0.01438  -0.1548   0.4239   1.0000
   8.250   1.6567   0.02292   0.01482  -0.1530   0.4212   1.0000
   8.500   1.6738   0.02328   0.01522  -0.1514   0.4186   1.0000
   8.750   1.6925   0.02361   0.01557  -0.1501   0.4162   1.0000
   9.000   1.7152   0.02391   0.01585  -0.1496   0.4139   1.0000
   9.250   1.7265   0.02444   0.01648  -0.1472   0.4110   1.0000
   9.500   1.7343   0.02505   0.01722  -0.1443   0.4077   1.0000
   9.750   1.7454   0.02560   0.01786  -0.1420   0.4044   1.0000
  10.000   1.7588   0.02608   0.01839  -0.1402   0.4014   1.0000
  10.250   1.7763   0.02647   0.01878  -0.1389   0.3987   1.0000
  10.500   1.7896   0.02706   0.01942  -0.1372   0.3958   1.0000
  10.750   1.7907   0.02808   0.02062  -0.1339   0.3919   1.0000
  11.000   1.7966   0.02898   0.02163  -0.1314   0.3883   1.0000
  11.250   1.8064   0.02974   0.02244  -0.1295   0.3849   1.0000
  11.500   1.8232   0.03022   0.02291  -0.1284   0.3819   1.0000
  11.750   1.8203   0.03175   0.02462  -0.1254   0.3778   1.0000
  12.000   1.8190   0.03333   0.02634  -0.1228   0.3734   1.0000
  12.250   1.8245   0.03455   0.02762  -0.1210   0.3694   1.0000
  12.500   1.8375   0.03532   0.02839  -0.1199   0.3657   1.0000
  12.750   1.8241   0.03810   0.03138  -0.1171   0.3605   1.0000
  13.000   1.8213   0.04022   0.03360  -0.1152   0.3554   1.0000
  13.250   1.8325   0.04123   0.03460  -0.1142   0.3512   1.0000
  13.500   1.8123   0.04521   0.03880  -0.1120   0.3450   1.0000
  13.750   1.8095   0.04771   0.04137  -0.1108   0.3393   1.0000
  14.000   1.8065   0.05036   0.04408  -0.1097   0.3339   1.0000
  14.250   1.7875   0.05490   0.04877  -0.1085   0.3268   1.0000
  14.500   1.7966   0.05634   0.05020  -0.1079   0.3215   1.0000
  14.750   1.7654   0.06273   0.05678  -0.1071   0.3131   1.0000
  15.000   1.7740   0.06431   0.05834  -0.1066   0.3071   1.0000
  15.250   1.7440   0.07097   0.06515  -0.1063   0.2979   1.0000
  15.500   1.7463   0.07347   0.06767  -0.1060   0.2913   1.0000
  15.750   1.7272   0.07900   0.07330  -0.1061   0.2821   1.0000
  16.000   1.7208   0.08283   0.07717  -0.1061   0.2743   1.0000
  16.250   1.7166   0.08638   0.08075  -0.1061   0.2660   1.0000
  16.500   1.7056   0.09102   0.08545  -0.1065   0.2573   1.0000
  16.750   1.7105   0.09328   0.08768  -0.1064   0.2497   1.0000
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