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Type of Document	Dissertation
Author	Tracy, Richard R.
URN	etd-10042002-161203
Persistent URL	http://resolver.caltech.edu/CaltechETD:etd-10042002-161203
Title	Hypersonic flow over a yawed circular cone
Degree	PhD
Option	Aeronautics
Advisory Committee	Advisor Name Title unknown Committee Member
Keywords	unknown
Date of Defense	1964-01-01
Availability	unrestricted
Abstract NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. A 10[degree] semi-apex, circular cone is tested in air at Mach 8 and at yaw angles to 24[degrees]; surface pressure, heat transfer, and pitot-pressure throughout the flow field are presented. The nominal surface temperature is 40% of the free stream stagnation temperature, and the Reynolds number, based on cone generator length, is varied from 0.5 x 10[^5] to 4.2 x 10[^5]. Heat transfer is measured at higher surface temperature ratios (up to 56%) and Reynolds numbers (up to 7.3 x 10[^5]) by reducing the free stream stagnation temperature. All raw data consist of continuous circumferential distributions of each quantity and are included in a supplement. The surface pressure data are compared with the theories of Stone-Kopal and Cheng; Reshotko's theory of heat transfer to the windward generator is compared with experiment. The probe data delineate the boundary between viscous and inviscid flow and determine the shape of the outer shock wave as well as the secondary shocks which appear in the flow field at large yaw. The probe data are sufficient to determine the flow field in the plane of symmetry and permit an approximate representation of the Mach number profiles of the separated viscous flow in the leeward meridian plane beyond a moderate yaw angle.
Files	Filename       Size       Approximate Download Time (Hours:Minutes:Seconds)     28.8 Modem   56K Modem   ISDN (64 Kb)   ISDN (128 Kb)   Higher-speed Access    Tracy_rr_1964.pdf 5.13 Mb 00:23:43 00:12:12 00:10:40 00:05:20 00:00:27