Yusi Shih

Graduation Semester and Year

2010

Language

English

Document Type

Thesis

Degree Name

Master of Science in Aerospace Engineering

Department

Mechanical and Aerospace Engineering

First Advisor

Frank Lu

Abstract

Shock wave/boundary layer interactions (SBLIs) are always an important issue for high-speed vehicles. SBLIs reduce the performance of aerodynamic surfaces and engine inlets, amongst a number of adverse effects. Micro-vortex generators (MVGs) are a potential flow control method that has seen intense investigation recently and have even been implemented in actual configurations at low speeds. The present research is focused on the mean pressures at Mach 2.5 around an MVG. Experiments were performed with a baseline flat plate and also with two MVG configurations (70 and 45 trailing edge) mounted ahead of a 5° ramp. In the present study MVGs are used to manipulated the flow within the boundary layer and the effects on the weak oblique shock produced by the 5° ramp are recorded. The results appeared similar to the large eddy simulations reported by Li and Liu [1] and [2]. Three conclusions can be made in present research 1. The different behaviors of SBLI, with MVG and without MVG, were observed from mean pressure measurements. 2. The mean pressure right behind MVG is lower, compared to the mean pressure in the middle of two MVGs. 3. The trailing angle of the MVG does affect the mean pressure distribution.

Disciplines

Aerospace Engineering | Engineering | Mechanical Engineering

Comments

Degree granted by The University of Texas at Arlington

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