Hypersonic flow over a yawed circular cone

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 p...

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Main Author: Tracy, Richard R.
Format: Others
Published: 1964
Online Access:https://thesis.library.caltech.edu/3903/1/Tracy_rr_1964.pdf
Tracy, Richard R. (1964) Hypersonic flow over a yawed circular cone. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/RMWT-TH67. https://resolver.caltech.edu/CaltechETD:etd-10042002-161203 <https://resolver.caltech.edu/CaltechETD:etd-10042002-161203>
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spelling ndltd-CALTECH-oai-thesis.library.caltech.edu-39032019-12-22T03:08:17Z Hypersonic flow over a yawed circular cone Tracy, Richard R. 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. 1964 Thesis NonPeerReviewed application/pdf https://thesis.library.caltech.edu/3903/1/Tracy_rr_1964.pdf https://resolver.caltech.edu/CaltechETD:etd-10042002-161203 Tracy, Richard R. (1964) Hypersonic flow over a yawed circular cone. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/RMWT-TH67. https://resolver.caltech.edu/CaltechETD:etd-10042002-161203 <https://resolver.caltech.edu/CaltechETD:etd-10042002-161203> https://thesis.library.caltech.edu/3903/
collection NDLTD
format Others
sources NDLTD
description 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.
author Tracy, Richard R.
spellingShingle Tracy, Richard R.
Hypersonic flow over a yawed circular cone
author_facet Tracy, Richard R.
author_sort Tracy, Richard R.
title Hypersonic flow over a yawed circular cone
title_short Hypersonic flow over a yawed circular cone
title_full Hypersonic flow over a yawed circular cone
title_fullStr Hypersonic flow over a yawed circular cone
title_full_unstemmed Hypersonic flow over a yawed circular cone
title_sort hypersonic flow over a yawed circular cone
publishDate 1964
url https://thesis.library.caltech.edu/3903/1/Tracy_rr_1964.pdf
Tracy, Richard R. (1964) Hypersonic flow over a yawed circular cone. Dissertation (Ph.D.), California Institute of Technology. doi:10.7907/RMWT-TH67. https://resolver.caltech.edu/CaltechETD:etd-10042002-161203 <https://resolver.caltech.edu/CaltechETD:etd-10042002-161203>
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