Abstract

A new shock tube test section has been designed and manufactured for the purpose of increasing the test time and expanding the applications of the shock tube for a multitude of ongoing and future projects. One purpose for the test section extension is to allow for flow visualization of droplets impacted by a shock wave for the interaction of hypersonic vehicles and atmospheric disturbances. Another purpose is to measure behind the incident shock to capture the chemical kinetics for a high-altitude environment and low-pressure, high-temperature space applications. This new test section contains 24 round optical ports for laser spectroscopy for multiple measurement locations in addition to 3 rectangular ports upstream for introducing and imaging droplets in the tube. StanShock was used to simulate the expected test time for the desired temperatures and pressures. This was compared against theoretical calculations of test time as a function of distance and velocity of the shock. The optimal length of the extension of 5 feet was then determined based on minimum required test time and limitations of the physical lab space.

Notes

If this is your thesis or dissertation, and want to learn how to access it or for more information about readership statistics, contact us at STARS@ucf.edu

Graduation Date

2022

Semester

Fall

Advisor

Vasu Sumathi, Subith

Degree

Master of Science in Aerospace Engineering (M.S.A.E.)

College

College of Engineering and Computer Science

Department

Mechanical and Aerospace Engineering

Degree Program

Aerospace Engineering; Thermofluid Aerodynamic Systems

Format

application/pdf

Identifier

CFE0009356; DP0027079

URL

https://purls.library.ucf.edu/go/DP0027079

Language

English

Release Date

December 2023

Length of Campus-only Access

1 year

Access Status

Masters Thesis (Open Access)

Download

Share

COinS