KENNEDY AND MARSDEN AIRFOIL (kenmar-il)
KENNEDY AND MARSDEN AIRFOIL - University of Alberta/Kennedy and Marsden high lift airfoil
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kenmar-il | 50,000 | 9 | 3 at α=16° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 50,000 | 5 | 3.5 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 9 | 3 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 100,000 | 5 | 4.7 at α=-8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 9 | 5.1 at α=-7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 200,000 | 5 | 17.1 at α=-0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 9 | 28.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 500,000 | 5 | 59 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 9 | 70.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kenmar-il | 1,000,000 | 5 | 97.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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