Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

KENNEDY AND MARSDEN AIRFOIL (kenmar-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: KENNEDY AND MARSDEN AIRFOIL (kenmar-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.09 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kenmar-il-1000000.txt
Download as CSV file: xf-kenmar-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.1042   0.05345   0.04763  -0.1835   0.4403   0.0415
 -13.250  -0.1203   0.04865   0.04271  -0.1869   0.4402   0.0415
 -13.000  -0.1267   0.04524   0.03921  -0.1892   0.4402   0.0416
 -12.750  -0.1289   0.04248   0.03636  -0.1908   0.4401   0.0417
 -12.500  -0.1275   0.04021   0.03403  -0.1920   0.4400   0.0418
 -12.250  -0.1245   0.03824   0.03199  -0.1928   0.4398   0.0419
 -12.000  -0.1190   0.03658   0.03027  -0.1934   0.4397   0.0420
 -11.750  -0.1119   0.03514   0.02878  -0.1937   0.4396   0.0421
 -11.500  -0.1041   0.03383   0.02743  -0.1938   0.4394   0.0423
 -11.250  -0.0956   0.03263   0.02619  -0.1938   0.4393   0.0424
 -11.000  -0.0853   0.03161   0.02513  -0.1936   0.4391   0.0426
 -10.750  -0.0748   0.03066   0.02414  -0.1933   0.4389   0.0428
 -10.500  -0.0634   0.02977   0.02321  -0.1929   0.4387   0.0430
 -10.250  -0.0519   0.02894   0.02234  -0.1924   0.4386   0.0432
 -10.000  -0.0397   0.02815   0.02152  -0.1918   0.4384   0.0433
  -9.750  -0.0268   0.02743   0.02075  -0.1911   0.4382   0.0435
  -9.500  -0.0139   0.02673   0.02002  -0.1903   0.4380   0.0436
  -9.250  -0.0001   0.02610   0.01937  -0.1894   0.4378   0.0437
  -9.000   0.0141   0.02553   0.01877  -0.1884   0.4376   0.0438
  -8.750   0.0280   0.02498   0.01819  -0.1873   0.4374   0.0439
  -8.500   0.0419   0.02449   0.01767  -0.1861   0.4372   0.0441
  -8.250   0.0560   0.02403   0.01720  -0.1848   0.4370   0.0441
  -8.000   0.0689   0.02362   0.01677  -0.1833   0.4368   0.0442
  -7.750   0.0796   0.02328   0.01642  -0.1812   0.4366   0.0443
  -7.500   0.0886   0.02302   0.01614  -0.1789   0.4364   0.0444
  -7.250   0.1019   0.02272   0.01584  -0.1772   0.4362   0.0445
  -7.000   0.1180   0.02240   0.01550  -0.1760   0.4359   0.0446
  -6.750   0.1356   0.02210   0.01518  -0.1751   0.4356   0.0446
  -6.500   0.1518   0.02157   0.01464  -0.1736   0.4352   0.0448
  -6.250   0.1684   0.02111   0.01418  -0.1722   0.4349   0.0451
  -6.000   0.1866   0.02071   0.01378  -0.1713   0.4347   0.0454
  -5.750   0.2070   0.02038   0.01346  -0.1707   0.4344   0.0456
  -5.500   0.2292   0.02008   0.01317  -0.1705   0.4341   0.0458
  -5.250   0.2532   0.01981   0.01291  -0.1705   0.4338   0.0461
  -5.000   0.2786   0.01957   0.01267  -0.1708   0.4336   0.0464
  -4.750   0.3053   0.01935   0.01245  -0.1713   0.4333   0.0467
  -4.500   0.3331   0.01914   0.01225  -0.1719   0.4330   0.0470
  -4.250   0.3620   0.01895   0.01206  -0.1727   0.4327   0.0474
  -4.000   0.3918   0.01879   0.01190  -0.1737   0.4324   0.0478
  -3.750   0.4223   0.01863   0.01174  -0.1747   0.4321   0.0482
  -3.500   0.4534   0.01850   0.01161  -0.1758   0.4318   0.0487
  -3.250   0.4845   0.01842   0.01152  -0.1768   0.4314   0.0492
  -3.000   0.5155   0.01834   0.01143  -0.1778   0.4311   0.0496
  -2.750   0.5468   0.01822   0.01131  -0.1788   0.4307   0.0499
  -2.500   0.5819   0.01792   0.01100  -0.1808   0.4302   0.0508
  -2.250   0.6157   0.01777   0.01086  -0.1823   0.4298   0.0516
  -2.000   0.6488   0.01769   0.01078  -0.1836   0.4293   0.0524
  -1.750   0.6822   0.01764   0.01072  -0.1850   0.4290   0.0531
  -1.500   0.7157   0.01761   0.01069  -0.1863   0.4286   0.0539
  -1.250   0.7491   0.01762   0.01070  -0.1876   0.4282   0.0549
  -1.000   0.7835   0.01763   0.01071  -0.1892   0.4279   0.0559
  -0.750   0.8196   0.01763   0.01072  -0.1911   0.4276   0.0578
  -0.500   0.8539   0.01769   0.01079  -0.1926   0.4272   0.0596
  -0.250   0.8879   0.01778   0.01089  -0.1940   0.4269   0.0619
   0.000   0.9240   0.01786   0.01100  -0.1960   0.4265   0.0661
   0.250   0.9600   0.01798   0.01116  -0.1979   0.4261   0.0729
   0.500   0.9993   0.01812   0.01139  -0.2006   0.4256   0.0937
   0.750   1.0499   0.01823   0.01178  -0.2059   0.4250   0.1713
   1.000   1.0882   0.01984   0.01372  -0.2095   0.4231   0.2450
   1.250   1.1399   0.01967   0.01380  -0.2149   0.4229   0.3321
   1.500   1.2117   0.01939   0.01394  -0.2245   0.4228   0.4980
   1.750   1.2503   0.01947   0.01416  -0.2268   0.4226   0.5593
   2.000   1.2802   0.01964   0.01437  -0.2273   0.4224   0.5808
   2.250   1.3085   0.01983   0.01459  -0.2275   0.4223   0.5944
   2.500   1.3357   0.02003   0.01480  -0.2274   0.4221   0.6071
   2.750   1.3620   0.02024   0.01504  -0.2272   0.4219   0.6162
   3.000   1.3862   0.02049   0.01531  -0.2266   0.4217   0.6256
   3.250   1.4108   0.02078   0.01560  -0.2260   0.4214   0.6330
   3.500   1.4341   0.02099   0.01586  -0.2252   0.4211   0.6399
   3.750   1.4572   0.02123   0.01613  -0.2245   0.4209   0.6433
   4.000   1.4805   0.02147   0.01639  -0.2238   0.4205   0.6465
   4.250   1.5037   0.02173   0.01666  -0.2231   0.4202   0.6498
   4.500   1.5264   0.02200   0.01694  -0.2223   0.4198   0.6534
   4.750   1.5482   0.02229   0.01725  -0.2214   0.4195   0.6563
   5.000   1.5704   0.02251   0.01749  -0.2206   0.4191   0.6604
   5.250   1.5887   0.02274   0.01776  -0.2190   0.4186   0.6631
   5.500   1.6084   0.02301   0.01806  -0.2178   0.4182   0.6651
   5.750   1.6292   0.02328   0.01835  -0.2168   0.4178   0.6667
   6.000   1.6504   0.02356   0.01865  -0.2160   0.4173   0.6682
   6.250   1.6716   0.02385   0.01895  -0.2151   0.4169   0.6697
   6.500   1.6915   0.02414   0.01927  -0.2141   0.4164   0.6713
   6.750   1.7104   0.02445   0.01960  -0.2129   0.4159   0.6729
   7.000   1.7291   0.02477   0.01994  -0.2117   0.4155   0.6746
   7.250   1.7479   0.02508   0.02027  -0.2105   0.4150   0.6762
   7.500   1.7665   0.02539   0.02060  -0.2094   0.4145   0.6776
   7.750   1.7848   0.02568   0.02090  -0.2082   0.4141   0.6788
   8.000   1.8037   0.02592   0.02116  -0.2072   0.4136   0.6798
   8.250   1.8227   0.02620   0.02144  -0.2061   0.4132   0.6806
   8.500   1.8419   0.02649   0.02175  -0.2052   0.4127   0.6815
   8.750   1.8632   0.02678   0.02205  -0.2047   0.4123   0.6838
   9.000   1.8827   0.02709   0.02238  -0.2039   0.4119   0.6854
   9.250   1.9014   0.02741   0.02273  -0.2030   0.4115   0.6870
   9.500   1.9203   0.02775   0.02308  -0.2021   0.4112   0.6886
   9.750   1.9400   0.02807   0.02342  -0.2013   0.4107   0.6900
  10.000   1.9592   0.02845   0.02381  -0.2006   0.4103   0.6913
  10.250   1.9790   0.02885   0.02422  -0.2000   0.4099   0.6926
  10.500   1.9970   0.02938   0.02477  -0.1991   0.4093   0.6940
  10.750   1.9787   0.03212   0.02762  -0.1943   0.4074   0.6951
  11.000   1.9819   0.03305   0.02862  -0.1919   0.4070   0.6964
  11.250   1.9806   0.03429   0.02994  -0.1893   0.4065   0.6977
  11.500   1.9740   0.03595   0.03168  -0.1865   0.4058   0.6988
  11.750   1.9530   0.03872   0.03457  -0.1830   0.4044   0.6999
  12.000   1.8008   0.05362   0.04985  -0.1763   0.3983   0.7000
  12.250   1.8155   0.05482   0.05106  -0.1765   0.3975   0.7011
  12.500   1.8355   0.05545   0.05169  -0.1766   0.3969   0.7022
  12.750   1.8573   0.05588   0.05211  -0.1767   0.3964   0.7032
  13.000   1.8806   0.05613   0.05235  -0.1769   0.3960   0.7041
  13.250   1.9064   0.05622   0.05244  -0.1772   0.3956   0.7057
  13.500   1.9336   0.05615   0.05237  -0.1776   0.3952   0.7076
  13.750   1.9572   0.05635   0.05257  -0.1778   0.3946   0.7092
  14.000   1.4221   0.11821   0.11494  -0.1702   0.3444   0.7032
<< Back to KENNEDY AND MARSDEN AIRFOIL (kenmar-il)

Polar data table (+)

Polar graphs


<< Back to KENNEDY AND MARSDEN AIRFOIL (kenmar-il)