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Modelling Rarefied Hypersonic Reactive Flows Using the Direct Simulation Monte Carlo Method

Published online by Cambridge University Press:  15 October 2015

Ming-Chung Lo
Affiliation:
Department of Mechanical Engineering, National Chiao Tung University, 1001 Ta-Hsueh Road, Hsinchu 30010, Taiwan
Cheng-Chin Su
Affiliation:
Department of Mechanical Engineering, National Chiao Tung University, 1001 Ta-Hsueh Road, Hsinchu 30010, Taiwan
Jong-Shinn Wu*
Affiliation:
Department of Mechanical Engineering, National Chiao Tung University, 1001 Ta-Hsueh Road, Hsinchu 30010, Taiwan
Kun-Chang Tseng
Affiliation:
National Space Organisation, National Applied Research Laboratories, Hsinchu 30010, Taiwan
*
*Corresponding author. Email addresses: mingchungluo@gmail.com (M.-C. Lo), ccs1982.me95g@gmail.com (C.-C. Su), chongsin@faculty.nctu.edu.tw (J.-S. Wu), kctseng@nspo.narl.org.tw (K.-C. Tseng)
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Abstract

This paper presents the implementation, validation and application of TCE (total collision energy) model for simulating hypersonic reactive flows in a parallel direct simulation Monte Carlo code, named PDSC++, using an unstructured grid. A series of benchmarking test cases, which include reproduction of theoretical rate constants in a single cell, 2D hypersonic flow past a cylinder and 2D-axisymmetric hypersonic flow past a sphere, were performed to validate the implementation. Finally, detailed aerothermodynamics of the flown reentry Apollo 6 Command Module at 105 km is simulated to demonstrate the powerful capability of the PDSC++ in treating realistic hypersonic reactive flow at high altitude.

Type
Research Article
Copyright
Copyright © Global-Science Press 2015 

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