ORCID

0009-0005-6305-6970

Keywords

optical diagnostics; shock tube; divert jet; jets in crossflow; hypersonics

Abstract

The present work explores using non-intrusive diagnostic techniques to investigate high-temperature, high-pressure environments in a shock tube facility. Shock tube facilities are generally used to achieve flow conditions similar to combustors or other supersonic flow regimes to study and validate chemical kinetics models. Traditional probes are unsuited to these extreme conditions due to their limited durability, poor spatial resolution, and slow response times. This study tested three techniques: Schlieren imaging, Background-Oriented Schlieren (BOS), and emission spectroscopy. Schlieren and BOS provide 2D visualization of the flowfield and density gradients with a temporal resolution of 10 μs. At the same time, emission spectroscopy offers complementary data on the chemical kinetics of the reacting flow. These non-intrusive methods allowed the observation of complex shock-driven phenomena, such as shock/jet interactions, without interfering with the flowfield. Improving the fundamental understanding of complex flowfields and validating the existing computational models allows for improving the design of future aerospace propulsion systems.

Completion Date

2024

Semester

Fall

Committee Chair

Vasu, Subith

Degree

Master of Science in Mechanical Engineering (M.S.M.E.)

College

College of Engineering and Computer Science

Department

Department of Mechanical and Aerospace Engineering

Format

PDF

Identifier

DP0029707

Document Type

Thesis

Campus Location

Orlando (Main) Campus

Subjects

Shock waves--Research; Aerothermodynamics--Research; Shock waves--Experiments; Gas dynamics--Research; Jets--Fluid dynamics--Research

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