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KENNEDY AND MARSDEN AIRFOIL (kenmar-il)

KENNEDY AND MARSDEN AIRFOIL - University of Alberta/Kennedy and Marsden high lift airfoil


Airfoil kenmar-il
Details Dat file Parser  
(kenmar-il) KENNEDY AND MARSDEN AIRFOIL
University of Alberta/Kennedy and Marsden high lift airfoil
Max thickness 27.9% at 31% chord.
Max camber 7.7% at 36.9% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 KENNEDY AND MARSDEN AIRFOIL
       51.       51.

 0.0000000 0.0000000
 0.0006922 0.0100844
 0.0032703 0.0226752
 0.0078138 0.0354134
 0.0142729 0.0486478
 0.0226258 0.0624277
 0.0328509 0.0764626
 0.0449126 0.0906212
 0.0587555 0.1047421
 0.0743339 0.1186733
 0.0915824 0.1322634
 0.1104454 0.1453605
 0.1308565 0.1578425
 0.1527206 0.1695470
 0.1759617 0.1803309
 0.2004945 0.1900625
 0.2262233 0.1985582
 0.2530441 0.2056456
 0.2808731 0.2110915
 0.3096004 0.2145630
 0.3391219 0.2155268
 0.3693302 0.2138892
 0.4001532 0.2083783
 0.4314359 0.1994891
 0.4629933 0.1897578
 0.4946885 0.1797704
 0.5263841 0.1697630
 0.5579469 0.1598516
 0.5892560 0.1500728
 0.6201894 0.1404734
 0.6506370 0.1310796
 0.6804584 0.1218978
 0.7095528 0.1129447
 0.7378002 0.1042370
 0.7650806 0.0957611
 0.7913039 0.0875244
 0.8163597 0.0795437
 0.8401480 0.0718158
 0.8625789 0.0643387
 0.8835720 0.0571295
 0.9030275 0.0501755
 0.9208748 0.0434947
 0.9370538 0.0370951
 0.9514940 0.0309948
 0.9641446 0.0252222
 0.9749446 0.0198057
 0.9838531 0.0147741
 0.9908355 0.0102964
 0.9958785 0.0061421
 0.9989334 0.0025900
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0013980 -.0138050
 0.0047754 -.0282722
 0.0100915 -.0416824
 0.0172333 -.0515577
 0.0261887 -.0581687
 0.0369440 -.0620757
 0.0495055 -.0648295
 0.0638290 -.0669816
 0.0798718 -.0687733
 0.0975622 -.0701367
 0.1168389 -.0710433
 0.1376331 -.0715255
 0.1598457 -.0716062
 0.1833956 -.0712674
 0.2081936 -.0705218
 0.2341399 -.0693827
 0.2611263 -.0679131
 0.2890636 -.0661255
 0.3178326 -.0640633
 0.3473143 -.0617504
 0.3773983 -.0591797
 0.4079735 -.0563045
 0.4388972 -.0530489
 0.4700573 -.0493263
 0.5013304 -.0450300
 0.5325842 -.0400840
 0.5636876 -.0344422
 0.5945206 -.0281180
 0.6249662 -.0211949
 0.6549217 -.0139360
 0.6842567 -.0066651
 0.7128826 0.0002449
 0.7406880 0.0065004
 0.7675580 0.0119084
 0.7934063 0.0163661
 0.8181233 0.0198503
 0.8416089 0.0223681
 0.8637721 0.0239568
 0.8845317 0.0246441
 0.9037864 0.0244871
 0.9214628 0.0235935
 0.9374980 0.0220617
 0.9518209 0.0199297
 0.9643791 0.0172858
 0.9751081 0.0142682
 0.9839628 0.0110657
 0.9909068 0.0078875
 0.9959198 0.0047327
 0.9989451 0.0021601
 1.0000000 0.0000000
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Polars for KENNEDY AND MARSDEN AIRFOIL (kenmar-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   kenmar-il50,00093 at α=16°Mach=0 Ncrit=9Xfoil predictionDetails
   kenmar-il50,00053.5 at α=15°Mach=0 Ncrit=5Xfoil predictionDetails
   kenmar-il100,00093 at α=14°Mach=0 Ncrit=9Xfoil predictionDetails
   kenmar-il100,00054.7 at α=-8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   kenmar-il200,00095.1 at α=-7°Mach=0 Ncrit=9Xfoil predictionDetails
   kenmar-il200,000517.1 at α=-0.75°Mach=0 Ncrit=5Xfoil predictionDetails
   kenmar-il500,000928.3 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   kenmar-il500,000559 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   kenmar-il1,000,000970.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   kenmar-il1,000,000597.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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