Graduation Semester and Year

2012

Language

English

Document Type

Thesis

Degree Name

Master of Engineering in Mechanical Engineering

Department

Mechanical and Aerospace Engineering

First Advisor

Donald R Wilson

Abstract

In hypersonic wind tunnel testing, matching the flow enthalpy conditions for the hypersonic air-breathing corridor is of great importance in order to assure the validity of experimental results. The flow enthalpy of the UTA hypersonic shock tunnel is increased by a shock induced detonation driver. The detonation mixture consist of hydrogen and oxygen in stoichiometric quantities ( 2H2+O2 ? 2H2O). Experimental variations of pressure and the volume of the detonation section were performed to characterize the enthalpy limits, and overall performance of the UTA hypersonic shock tunnel. The UTA HST test section is designed for a nominal Mach number of 10. Force balance experiments were performed in the test section during the high enthalpy characterization. Enthalpy measurements were also performed using a type K thermocouple placed in a Fay-Riddell probe within the test section. High enthalpy flows with maximum total temperature of 4393oK, maximum total pressure of 373 atm, and maximum total enthalpy of 5.1 MJ/Kg are achieved in the driven section, with Mach numbers of 8.75 0.25 measured in the test section.

Disciplines

Aerospace Engineering | Engineering | Mechanical Engineering

Comments

Degree granted by The University of Texas at Arlington

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