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.
Original language | English |
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Pages (from-to) | 1095-1121 |
Number of pages | 27 |
Journal | Communications in Computational Physics |
Volume | 18 |
Issue number | 4 |
DOIs | |
State | Published - 15 Oct 2015 |
Keywords
- DSMC
- TCE (total collision energy)
- chemistry
- hypersonic
- non-equilibrium