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KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: KENNEDY AND MARSDEN AIRFOIL (kenmar-il)
Reynolds number: 500,000
Max Cl/Cd: 59.01 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kenmar-il-500000-n5.txt
Download as CSV file: xf-kenmar-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.0817   0.06339   0.05626  -0.1718   0.4384   0.0400
 -13.500  -0.1007   0.05772   0.05046  -0.1757   0.4383   0.0401
 -13.250  -0.1095   0.05359   0.04623  -0.1785   0.4382   0.0402
 -13.000  -0.1133   0.05024   0.04280  -0.1807   0.4380   0.0402
 -12.750  -0.1137   0.04742   0.03990  -0.1825   0.4379   0.0403
 -12.500  -0.1114   0.04503   0.03744  -0.1839   0.4377   0.0404
 -12.250  -0.1075   0.04291   0.03527  -0.1849   0.4375   0.0405
 -12.000  -0.1020   0.04104   0.03335  -0.1858   0.4373   0.0406
 -11.750  -0.0951   0.03940   0.03166  -0.1864   0.4370   0.0407
 -11.500  -0.0872   0.03791   0.03013  -0.1868   0.4368   0.0408
 -11.250  -0.0787   0.03656   0.02873  -0.1870   0.4366   0.0409
 -11.000  -0.0695   0.03534   0.02747  -0.1871   0.4363   0.0410
 -10.750  -0.0596   0.03424   0.02634  -0.1870   0.4361   0.0411
 -10.500  -0.0492   0.03322   0.02529  -0.1868   0.4358   0.0412
 -10.250  -0.0383   0.03228   0.02431  -0.1864   0.4356   0.0414
 -10.000  -0.0268   0.03142   0.02342  -0.1859   0.4353   0.0415
  -9.750  -0.0152   0.03060   0.02257  -0.1854   0.4350   0.0416
  -9.500  -0.0028   0.02986   0.02180  -0.1847   0.4347   0.0418
  -9.250   0.0096   0.02916   0.02108  -0.1839   0.4345   0.0419
  -9.000   0.0220   0.02850   0.02039  -0.1830   0.4342   0.0421
  -8.750   0.0349   0.02790   0.01977  -0.1820   0.4339   0.0422
  -8.500   0.0477   0.02733   0.01918  -0.1809   0.4336   0.0424
  -8.250   0.0601   0.02679   0.01861  -0.1796   0.4333   0.0426
  -8.000   0.0725   0.02629   0.01809  -0.1782   0.4331   0.0427
  -7.750   0.0846   0.02582   0.01761  -0.1767   0.4328   0.0429
  -7.500   0.0956   0.02538   0.01715  -0.1749   0.4325   0.0431
  -7.250   0.1050   0.02497   0.01673  -0.1728   0.4323   0.0433
  -7.000   0.1124   0.02463   0.01639  -0.1702   0.4320   0.0434
  -6.750   0.1190   0.02433   0.01607  -0.1675   0.4317   0.0436
  -6.500   0.1308   0.02398   0.01570  -0.1657   0.4315   0.0437
  -6.250   0.1449   0.02364   0.01535  -0.1642   0.4312   0.0439
  -6.000   0.1608   0.02331   0.01501  -0.1630   0.4309   0.0441
  -5.750   0.1781   0.02299   0.01467  -0.1621   0.4306   0.0443
  -5.500   0.1974   0.02270   0.01436  -0.1614   0.4304   0.0445
  -5.250   0.2175   0.02237   0.01403  -0.1609   0.4301   0.0448
  -5.000   0.2384   0.02200   0.01367  -0.1606   0.4298   0.0452
  -4.750   0.2614   0.02168   0.01336  -0.1606   0.4294   0.0456
  -4.500   0.2861   0.02140   0.01308  -0.1608   0.4290   0.0460
  -4.250   0.3122   0.02114   0.01282  -0.1613   0.4287   0.0464
  -4.000   0.3394   0.02091   0.01258  -0.1618   0.4283   0.0467
  -3.750   0.3679   0.02070   0.01237  -0.1626   0.4280   0.0471
  -3.500   0.3973   0.02052   0.01219  -0.1635   0.4277   0.0476
  -3.250   0.4274   0.02037   0.01202  -0.1645   0.4274   0.0480
  -3.000   0.4580   0.02024   0.01189  -0.1656   0.4271   0.0486
  -2.750   0.4889   0.02013   0.01176  -0.1666   0.4268   0.0491
  -2.500   0.5201   0.02006   0.01168  -0.1677   0.4265   0.0496
  -2.250   0.5522   0.01997   0.01159  -0.1690   0.4262   0.0502
  -2.000   0.5851   0.01990   0.01154  -0.1704   0.4259   0.0510
  -1.750   0.6179   0.01988   0.01153  -0.1718   0.4256   0.0518
  -1.500   0.6506   0.01991   0.01156  -0.1731   0.4253   0.0527
  -1.250   0.6836   0.01997   0.01162  -0.1745   0.4249   0.0539
  -1.000   0.7166   0.02008   0.01172  -0.1758   0.4244   0.0550
  -0.750   0.7504   0.02026   0.01192  -0.1774   0.4237   0.0565
  -0.500   0.7833   0.02052   0.01222  -0.1788   0.4231   0.0583
  -0.250   0.8144   0.02055   0.01227  -0.1798   0.4229   0.0607
   0.000   0.8461   0.02056   0.01231  -0.1809   0.4226   0.0638
   0.250   0.8773   0.02060   0.01239  -0.1819   0.4224   0.0678
   0.500   0.9094   0.02062   0.01247  -0.1831   0.4221   0.0741
   0.750   0.9423   0.02068   0.01260  -0.1845   0.4218   0.0849
   1.000   0.9775   0.02073   0.01276  -0.1864   0.4216   0.1097
   1.250   1.0158   0.02077   0.01297  -0.1891   0.4213   0.1511
   1.500   1.0570   0.02080   0.01321  -0.1924   0.4209   0.2077
   1.750   1.0994   0.02087   0.01347  -0.1959   0.4206   0.2694
   2.000   1.1495   0.02092   0.01378  -0.2011   0.4202   0.3546
   2.250   1.2174   0.02096   0.01434  -0.2100   0.4198   0.5319
   2.500   1.2439   0.02127   0.01479  -0.2100   0.4194   0.5762
   2.750   1.2661   0.02161   0.01519  -0.2090   0.4190   0.5990
   3.000   1.2869   0.02194   0.01556  -0.2079   0.4185   0.6147
   3.250   1.3067   0.02229   0.01595  -0.2065   0.4181   0.6239
   3.500   1.3301   0.02261   0.01626  -0.2060   0.4175   0.6300
   3.750   1.3531   0.02293   0.01658  -0.2054   0.4170   0.6345
   4.000   1.3718   0.02327   0.01697  -0.2040   0.4165   0.6385
   4.250   1.3902   0.02366   0.01740  -0.2025   0.4160   0.6429
   4.500   1.4084   0.02408   0.01785  -0.2011   0.4156   0.6481
   4.750   1.4283   0.02450   0.01828  -0.2000   0.4151   0.6528
   5.000   1.4494   0.02490   0.01869  -0.1993   0.4147   0.6556
   5.250   1.4706   0.02531   0.01909  -0.1987   0.4142   0.6571
   5.500   1.4896   0.02570   0.01951  -0.1976   0.4138   0.6586
   5.750   1.5079   0.02611   0.01995  -0.1965   0.4133   0.6600
   6.000   1.5257   0.02654   0.02041  -0.1953   0.4129   0.6615
   6.250   1.5429   0.02699   0.02089  -0.1940   0.4125   0.6631
   6.500   1.5601   0.02745   0.02137  -0.1928   0.4121   0.6647
   6.750   1.5773   0.02792   0.02186  -0.1917   0.4116   0.6662
   7.000   1.5946   0.02840   0.02237  -0.1906   0.4112   0.6676
   7.250   1.6121   0.02890   0.02288  -0.1896   0.4108   0.6691
   7.500   1.6292   0.02943   0.02342  -0.1886   0.4104   0.6706
   7.750   1.6470   0.02994   0.02395  -0.1878   0.4100   0.6721
   8.000   1.6642   0.03051   0.02453  -0.1869   0.4096   0.6736
   8.250   1.6817   0.03108   0.02512  -0.1861   0.4092   0.6753
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