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

Part of: Rarefied gas flows, Boltzmann equation

Published online by Cambridge University Press:  15 October 2015

Ming-Chung Lo ,
Cheng-Chin Su ,
Jong-Shinn Wu  and
Kun-Chang Tseng
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: [email protected] (M.-C. Lo), [email protected] (C.-C. Su), [email protected] (J.-S. Wu), [email protected] (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.

Keywords

DSMCchemistrynon-equilibriumTCE (total collision energy)hypersonic

MSC classification

Secondary: 76P05: Rarefied gas flows, Boltzmann equation
Type
Research Article
Information
Communications in Computational Physics , Volume 18 , Issue 4 , October 2015 , pp. 1095 - 1121
Copyright
Copyright © Global-Science Press 2015 

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