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KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: KENNEDY AND MARSDEN AIRFOIL (kenmar-il)
Reynolds number: 500,000
Max Cl/Cd: 28.26 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kenmar-il-500000.txt
Download as CSV file: xf-kenmar-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KENNEDY AND MARSDEN 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.4521   0.10671   0.10089  -0.1598   0.4559   0.0570
 -10.500   0.4631   0.10483   0.09904  -0.1606   0.4556   0.0576
 -10.250   0.2449   0.06254   0.05657  -0.1840   0.4572   0.0554
 -10.000   0.2663   0.06201   0.05611  -0.1827   0.4568   0.0550
  -9.750   0.1944   0.05093   0.04484  -0.1901   0.4570   0.0537
  -9.500   0.1436   0.04462   0.03829  -0.1928   0.4569   0.0530
  -9.250   0.1199   0.04120   0.03471  -0.1931   0.4567   0.0528
  -9.000   0.1093   0.03896   0.03234  -0.1925   0.4565   0.0528
  -8.750   0.1049   0.03728   0.03056  -0.1915   0.4563   0.0530
  -8.500   0.1019   0.03591   0.02909  -0.1900   0.4561   0.0531
  -8.250   0.0972   0.03493   0.02803  -0.1877   0.4559   0.0532
  -8.000   0.0934   0.03410   0.02712  -0.1850   0.4557   0.0532
  -7.750   0.0989   0.03321   0.02614  -0.1836   0.4554   0.0533
  -7.500   0.1086   0.03242   0.02527  -0.1825   0.4551   0.0534
  -7.250   0.1214   0.03173   0.02450  -0.1817   0.4548   0.0536
  -7.000   0.1364   0.03109   0.02380  -0.1809   0.4545   0.0537
  -6.750   0.1528   0.03055   0.02319  -0.1802   0.4542   0.0539
  -6.500   0.1704   0.03008   0.02267  -0.1794   0.4539   0.0540
  -6.250   0.1887   0.02969   0.02222  -0.1786   0.4535   0.0543
  -6.000   0.2077   0.02934   0.02183  -0.1777   0.4532   0.0545
  -5.750   0.2272   0.02905   0.02150  -0.1769   0.4528   0.0547
  -5.500   0.2476   0.02876   0.02118  -0.1761   0.4523   0.0549
  -5.250   0.2688   0.02850   0.02088  -0.1754   0.4517   0.0551
  -5.000   0.2906   0.02830   0.02064  -0.1748   0.4511   0.0553
  -4.750   0.3115   0.02809   0.02041  -0.1740   0.4507   0.0555
  -4.500   0.3292   0.02774   0.02009  -0.1723   0.4503   0.0559
  -4.250   0.3481   0.02753   0.01993  -0.1709   0.4499   0.0563
  -4.000   0.3688   0.02740   0.01984  -0.1700   0.4495   0.0567
  -3.750   0.3913   0.02728   0.01974  -0.1695   0.4490   0.0573
  -3.500   0.4142   0.02719   0.01966  -0.1690   0.4484   0.0579
  -3.250   0.4378   0.02713   0.01962  -0.1687   0.4479   0.0586
  -3.000   0.4616   0.02708   0.01957  -0.1684   0.4474   0.0593
  -2.750   0.4852   0.02708   0.01958  -0.1680   0.4469   0.0599
  -2.500   0.5094   0.02711   0.01962  -0.1678   0.4465   0.0604
  -2.250   0.5345   0.02717   0.01968  -0.1677   0.4461   0.0611
  -2.000   0.5599   0.02723   0.01974  -0.1678   0.4457   0.0617
  -1.750   0.5866   0.02717   0.01973  -0.1683   0.4453   0.0626
  -1.500   0.6145   0.02727   0.01986  -0.1690   0.4448   0.0636
  -1.250   0.6429   0.02746   0.02008  -0.1697   0.4443   0.0648
  -1.000   0.6715   0.02773   0.02036  -0.1705   0.4438   0.0661
  -0.750   0.6995   0.02815   0.02079  -0.1712   0.4433   0.0675
  -0.500   0.7276   0.02881   0.02150  -0.1722   0.4426   0.0693
  -0.250   0.7269   0.03131   0.02416  -0.1692   0.4407   0.0705
   0.000   0.7545   0.03123   0.02412  -0.1697   0.4403   0.0731
   0.250   0.7814   0.03127   0.02421  -0.1702   0.4398   0.0764
   0.500   0.8053   0.03155   0.02458  -0.1704   0.4393   0.0813
   0.750   0.8289   0.03194   0.02507  -0.1706   0.4387   0.0901
   1.000   0.8544   0.03235   0.02573  -0.1717   0.4379   0.1251
   1.250   0.8965   0.03279   0.02671  -0.1766   0.4368   0.2526
   1.500   0.9306   0.03367   0.02799  -0.1800   0.4357   0.3517
   1.750   0.9799   0.03467   0.02964  -0.1864   0.4345   0.5336
   2.000   0.9663   0.03663   0.03179  -0.1816   0.4329   0.5594
   2.250   0.9386   0.03932   0.03464  -0.1756   0.4310   0.5685
   2.500   0.9204   0.04191   0.03735  -0.1717   0.4294   0.5819
   2.750   0.9188   0.04380   0.03930  -0.1695   0.4282   0.5953
   3.000   0.9341   0.04485   0.04033  -0.1689   0.4276   0.6105
   3.250   0.9533   0.04535   0.04084  -0.1678   0.4271   0.6219
   3.500   0.9693   0.04631   0.04177  -0.1673   0.4264   0.6315
   3.750   0.9827   0.04717   0.04264  -0.1659   0.4258   0.6387
   4.000   0.9944   0.04812   0.04360  -0.1643   0.4251   0.6464
   4.250   1.0015   0.05003   0.04549  -0.1630   0.4242   0.6538
   4.500   0.6582   0.09252   0.08857  -0.1643   0.3925   0.5962
   4.750   0.6877   0.09227   0.08831  -0.1637   0.3930   0.6164
   5.000   0.6310   0.10214   0.09825  -0.1647   0.3825   0.6100
   5.250   0.6523   0.10258   0.09871  -0.1640   0.3821   0.6241
   5.500   0.6766   0.10288   0.09896  -0.1637   0.3817   0.6356
   5.750   0.6964   0.10320   0.09929  -0.1627   0.3813   0.6444
   6.000   0.7184   0.10354   0.09959  -0.1619   0.3810   0.6542
   6.250   0.7374   0.10393   0.09998  -0.1608   0.3807   0.6622
   6.500   0.7512   0.10441   0.10049  -0.1587   0.3802   0.6700
   6.750   0.7063   0.11312   0.10930  -0.1601   0.3693   0.6680
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