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Type of Document	Engineer's Thesis
Author	Nicholson, Kenneth F.
URN	etd-01242006-094259
Persistent URL	http://resolver.caltech.edu/CaltechETD:etd-01242006-094259
Title	The effects of blunt leading edges on delta wings at Mach 5.8
Degree	Engineer's Degree
Option	Aeronautics
Advisory Committee	Advisor Name Title Lester Lees Committee Chair
Keywords	none
Date of Defense	1958-01-01
Availability	unrestricted
Abstract NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. Pressure distributions were measured on a series of four delta wings with subsonic and supersonic leading edges, both sharp and blunt. The blunt leading edge radius was about 0.5 per cent of root chord. Schlieren studies were also made to determine top and side view shock locations. The tests were conducted at a nominal Mach number of 5.8, and at Reynolds numbers between 0.335 x 10(6) and 0.901 x 10(6) based on root chord. Angular settings covered a range [...] in pitch at zero yaw (about [...]), and a range of v/V = +/- 0.125 (about +/- 7.2°) at a fixed angle of pitch of 11.5°. The effects of bluntness were found to be small. Also, the pressures produced by shock wave interactions with the boundary layer, and the inviscid pressures generated by the blunt leading edges, were found to be small compared with the inviscid pressures producing lift on the basic wing. Spanwise pressure distributions show no similarity to those obtained by linearized theory. Centerline lower surface pressure in pitch at zero yaw is bracketed between the Newtonian value [...] and the two-dimensional exact value.
Files	Filename       Size       Approximate Download Time (Hours:Minutes:Seconds)     28.8 Modem   56K Modem   ISDN (64 Kb)   ISDN (128 Kb)   Higher-speed Access    Nicholson_kf_1958.pdf 14.33 Mb 01:06:19 00:34:06 00:29:50 00:14:55 00:01:16   Nicholson_kf_1958_Fig_14.pdf 8.21 Mb 00:38:01 00:19:33 00:17:06 00:08:33 00:00:43   Nicholson_kf_1958_Fig_15.pdf 7.43 Mb 00:34:23 00:17:41 00:15:28 00:07:44 00:00:39   Nicholson_kf_1958_Fig_17.pdf 8.07 Mb 00:37:21 00:19:12 00:16:48 00:08:24 00:00:43   Nicholson_kf_1958_Fig_22.pdf 6.60 Mb 00:30:32 00:15:42 00:13:44 00:06:52 00:00:35   Nicholson_kf_1958_Fig_25.pdf 6.12 Mb 00:28:18 00:14:33 00:12:44 00:06:22 00:00:32   Nicholson_kf_1958_Fig_36.pdf 6.41 Mb 00:29:41 00:15:16 00:13:21 00:06:40 00:00:34   Nicholson_kf_1958_Fig_37.pdf 6.06 Mb 00:28:02 00:14:25 00:12:37 00:06:18 00:00:32