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E63 (4.25%) (e63-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E63 (4.25%) (e63-il)
Reynolds number: 500,000
Max Cl/Cd: 176.79 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e63-il-500000.txt
Download as CSV file: xf-e63-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E63  (4.25%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3789   0.10888   0.10674  -0.0119   1.0000   0.0057
  -7.500  -0.3792   0.10675   0.10462  -0.0111   1.0000   0.0058
  -7.250  -0.3803   0.10473   0.10261  -0.0101   1.0000   0.0059
  -7.000  -0.3701   0.10180   0.09969  -0.0124   0.9986   0.0060
  -6.750  -0.3543   0.09847   0.09635  -0.0163   0.9960   0.0062
  -6.500  -0.3405   0.09533   0.09322  -0.0197   0.9925   0.0064
  -6.250  -0.3254   0.09205   0.08995  -0.0234   0.9886   0.0066
  -6.000  -0.3020   0.08810   0.08599  -0.0292   0.9860   0.0068
  -5.750  -0.2806   0.08426   0.08216  -0.0343   0.9821   0.0071
  -5.500  -0.2581   0.08031   0.07820  -0.0397   0.9776   0.0075
  -5.250  -0.2275   0.07602   0.07390  -0.0472   0.9750   0.0081
  -5.000  -0.1801   0.07138   0.06923  -0.0601   0.9734   0.0089
  -4.750  -0.1548   0.06774   0.06557  -0.0656   0.9668   0.0090
  -4.500  -0.1122   0.06282   0.06062  -0.0757   0.9646   0.0091
  -4.250  -0.0744   0.05570   0.05347  -0.0861   0.9632   0.0099
  -4.000  -0.0387   0.05214   0.04985  -0.0924   0.9623   0.0108
  -3.750  -0.0056   0.04866   0.04633  -0.0983   0.9574   0.0126
  -3.500   0.0477   0.04385   0.04142  -0.1091   0.9558   0.0139
  -3.250   0.1111   0.03912   0.03653  -0.1207   0.9552   0.0155
  -3.000   0.1676   0.03530   0.03252  -0.1292   0.9545   0.0161
  -2.750   0.2370   0.02774   0.02458  -0.1427   0.9562   0.0170
  -2.500   0.2820   0.02481   0.02150  -0.1488   0.9556   0.0190
  -2.250   0.3293   0.02227   0.01868  -0.1540   0.9552   0.0218
  -2.000   0.3717   0.02156   0.01768  -0.1562   0.9537   0.0267
  -1.250   0.5116   0.01393   0.00886  -0.1685   0.9548   0.0165
  -1.000   0.5550   0.01204   0.00673  -0.1716   0.9547   0.0142
  -0.750   0.5942   0.01132   0.00594  -0.1739   0.9531   0.0164
  -0.500   0.6352   0.01057   0.00510  -0.1766   0.9518   0.0217
  -0.250   0.6773   0.00977   0.00468  -0.1798   0.9507   0.1906
   0.000   0.7107   0.00813   0.00480  -0.1813   0.9499   1.0000
   0.250   0.7380   0.00799   0.00459  -0.1810   0.9428   1.0000
   0.500   0.7753   0.00771   0.00425  -0.1828   0.9396   1.0000
   0.750   0.8139   0.00738   0.00388  -0.1849   0.9373   1.0000
   1.000   0.8413   0.00721   0.00369  -0.1845   0.9291   1.0000
   1.250   0.8793   0.00685   0.00334  -0.1865   0.9248   1.0000
   1.500   0.9101   0.00666   0.00314  -0.1868   0.9144   1.0000
   1.750   0.9464   0.00645   0.00292  -0.1885   0.9038   1.0000
   2.000   0.9897   0.00621   0.00268  -0.1917   0.8896   1.0000
   2.250   1.0392   0.00605   0.00251  -0.1963   0.8658   1.0000
   2.500   1.0802   0.00611   0.00242  -0.1990   0.8257   1.0000
   2.750   1.1074   0.00656   0.00251  -0.1985   0.7529   1.0000
   3.000   1.1208   0.00748   0.00281  -0.1950   0.6398   1.0000
   3.250   1.1361   0.00835   0.00318  -0.1923   0.5431   1.0000
   3.500   1.1542   0.00919   0.00358  -0.1903   0.4550   1.0000
   3.750   1.1718   0.01023   0.00412  -0.1885   0.3484   1.0000
   4.000   1.1914   0.01122   0.00463  -0.1871   0.2550   1.0000
   4.250   1.2110   0.01230   0.00521  -0.1858   0.1627   1.0000
   4.500   1.2304   0.01347   0.00590  -0.1844   0.0783   1.0000
   4.750   1.2500   0.01471   0.00679  -0.1829   0.0201   1.0000
   5.000   1.2735   0.01535   0.00752  -0.1819   0.0165   1.0000
   5.250   1.2963   0.01609   0.00839  -0.1807   0.0151   1.0000
   5.500   1.3180   0.01702   0.00945  -0.1793   0.0145   1.0000
   5.750   1.3369   0.01836   0.01096  -0.1774   0.0136   1.0000
   6.000   1.3544   0.02007   0.01283  -0.1752   0.0131   1.0000
   6.250   1.3752   0.02129   0.01418  -0.1737   0.0129   1.0000
   6.500   1.3961   0.02277   0.01580  -0.1721   0.0127   1.0000
   6.750   1.4176   0.02465   0.01789  -0.1707   0.0123   1.0000
   7.000   1.4402   0.02706   0.02051  -0.1693   0.0121   1.0000
   7.250   1.4623   0.02858   0.02222  -0.1680   0.0111   1.0000
   7.500   1.4835   0.03164   0.02561  -0.1663   0.0109   1.0000
   7.750   1.5014   0.03564   0.03006  -0.1638   0.0108   1.0000
   8.250   1.4719   0.03978   0.03563  -0.1474   0.0105   1.0000
   8.500   1.4645   0.04698   0.04330  -0.1420   0.0111   1.0000
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