Date of Award

3-2025

Document Type

Thesis

Degree Name

Master of Science in Aeronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Robert B. MacDermott, PhD

Abstract

Accurately determining adiabatic wall temperature is critical for characterizing surface heating in hypersonic flows. The differences between adiabatic wall temperature and stagnation temperature for Mach 6 flow are examined. A two-dimensional explicit finite difference scheme was developed to analyze heat transfer within an angled wedge and to assess the applicability of the classical semi-infinite solid solution to the Fourier Heat Equation for estimating adiabatic wall temperature and convective heat transfer coefficients. Experimental surface temperature data were extracted from infrared thermography obtained during Mach 6 wind tunnel tests, and the semi-infinite solid solution was applied to estimate the adiabatic wall temperature. Comparisons between experimental results, theoretical predictions, and computational heat flux data reveal significant differences between the adiabatic wall temperature and stagnation temperature. Additionally, differences between analytical and experimental estimates of adiabatic wall temperature highlight challenges in accurately predicting heat transfer in hypersonic flow environments using analytical models. These findings enhance convective heat transfer techniques for high-speed aerodynamic applications.

AFIT Designator

AFIT-ENY-MS-25-M-134

DTIC Accession Number

AD1356380

Comments

An embargo was observed for posting this thesis.

Distribution A: Approved for Public Release, Distribution Unlimited.

PA clearance case 88ABW-2025-0379

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