Numerical Analysis of an Actively-Cooled Low-Reynolds Number Hypersonic Diffuser
This paper gives a comprehensive numerical analysis of a Low-Reynolds number hypersonic diffuser designed for the upgraded 1.6 MW Arc-Heated Wind Tunnel (AHWT-II) facility at the University of Texas at Arlington. The numerical study includes the detailed investigation of the high-temperature, viscous, chemically-reacting non-equilibrium hypersonic flow field inside the diffuser with high fidelity computational fluid dynamics (CFD) simulations at a number of diffuser exit pressure conditions. The CFD analysis is used to evaluate the overall performance of the configuration at selected operating conditions and provide wall heat flux values for the numerical analysis and design of an active cooling system for the thermal management of the diffuser. The CFD results are obtained with non-catalytic and fully-catalytic wall assumption to bound the estimated heat flux to the diffuser walls. Besides heat flux, the effect of surface catalyticity on the flow field is discussed. A detailed numerical analysis focusing on active cooling of the diffuser is presented.
A. J. Brune et al., "Numerical Analysis of an Actively-Cooled Low-Reynolds Number Hypersonic Diffuser," Proceedings of the 21st AIAA International Space Planes and Hypersonics Technologies Conference (2017, Xiamen, China), American Institute of Aeronautics and Astronautics (AIAA), Mar 2017.
21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017 (2017: Mar. 6-9, Xiamen, China)
Mechanical and Aerospace Engineering
Keywords and Phrases
Computational fluid dynamics; Flow fields; Hypersonic flow; Numerical analysis; Reynolds equation; Reynolds number; Spacecraft; Wind tunnels, Catalytic walls; Computational fluid dynamics simulations; High temperature; Low Reynolds number; Non equilibrium; Operating condition; Pressure conditions; University of Texas, Heat flux
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2017 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Mar 2017