ORCID

0000-0002-9371-4242

Keywords

Transpiration Cooling, Hypersonics, Modeling

Abstract

Hypersonic flight vehicles are a promising form of high speed passenger transport and efficient space access architectures. However, they are fundamentally a thermally limited technology. High heat fluxes exceeding 10 MW/m2 and gas temperatures between 3000-4000K can be found both within the engine, and on the outer surface. Current conventional engineering materials are non-viable at these conditions. In order to make these materials viable, active cooling strategies could be utilized. One particularly promising type is transpiration cooling, where a coolant is diffused through a porous surface. Although researched heavily in the 1960s, adoption is still minimal. Part of the reason is the requirement for a defect rich porous solid phase, which is intrinsically susceptible to mechanical failure. In the open literature there has been limited work on the thermal and mechanical design of porous transpiration surfaces. This work presents a coupled analytical model that predicts first order thermomechanical performance. Yielding from thermal stress dominates these systems, and counterintuitively decreases with increasing porosity. However, at these higher porosities, local deformation begins to become a concern. Coupled mass optimization between the solid and liquid phase is also examined with trade offs between high temperature alloys and lightweight, low temperature options.

Completion Date

2026

Semester

Spring

Committee Chair

Ahmed, Kareem

Degree

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

College

College of Engineering and Computer Science

Department

Mechanical and Aerospace Engineering

Document Type

Dissertation/Thesis

Identifier

DP0053137

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