Dissertation/Thesis Abstract

Simulation of a Barrel Shock in Underexpanded Supersonic Flow
by Howell, Tyler Latham, M.S., Mississippi State University, 2020, 144; 28028408
Abstract (Summary)

Two-dimensional supersonic flows out of rocket nozzles are one of three flow types: over-, perfectly-, or under-expanded. In under-expanded flows, an expansion fan is centered at the top and bottom tip of the rocket nozzle. When the waves from the expansion wave cross through the centerline and intersect the free boundary, the waves are reflected as compression waves. For higher exit-to-ambient pressure ratios, the compression waves coalesce and eventually form a barrel shock. The purpose of this study was to use the Method of Characteristics (MOC), a mathematical procedure for solving hyperbolic partial differential equations, to simulate the formation of the barrel shock. A MOC code was developed in the Python programming language to accomplish task. Results of the MOC code compared favorably with CFD results.

Indexing (document details)
Advisor: Thompson, David S
Commitee: Sescu, Adrian, Koenig, Keith
School: Mississippi State University
Department: Aerospace Engineering
School Location: United States -- Mississippi
Source: MAI 82/2(E), Masters Abstracts International
Source Type: DISSERTATION
Subjects: Aerospace engineering, Aeronomy
Keywords: Method of characteristics, Nozzle exhaust, Supersonic flow, Underexpanded flow
Publication Number: 28028408
ISBN: 9798662594890
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