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J. Marichalar, A. Prisbell, F. Lumpkin, G. LeBeau (2011)
Study of Plume Impingement Effects in the Lunar Lander Environment, 1333
G. Bird (1970)
Breakdown of translational and rotational equilibrium in gaseous expansionsAIAA Journal, 8
K. Kannenberg (1998)
Computational methods for the direct simulation Monte Carlo technique with application to plume impingement
D. Hash, H. Hassan (1996)
Assessment of schemes for coupling Monte Carlo and Navier-Stokes solution methodsJournal of Thermophysics and Heat Transfer, 10
Alejandro Garcia, B. Alder (1998)
Generation of the Chapman-Enskog DistributionJournal of Computational Physics, 140
V. Kolobov, R. Arslanbekov, V. Aristov, A. Frolova, S. Zabelok (2007)
Unified solver for rarefied and continuum flows with adaptive mesh and algorithm refinementJ. Comput. Phys., 223
W. Wang, I. Boyd (2003)
Predicting continuum breakdown in hypersonic viscous flowsPhysics of Fluids, 15
D. Wadsworth, D. Erwin (1992)
Two-dimensional hybrid continuum/particle approach for rarefied flows
T. Schwartzentruber, Leonardo Scalabrin, I. Boyd (2007)
A modular particle-continuum numerical method for hypersonic non-equilibrium gas flowsJ. Comput. Phys., 225
Bijiao He, Xiaoying He, Mingxing Zhang, Guobiao Cai (2013)
Plume aerodynamic effects of cushion engine in lunar landingChinese Journal of Aeronautics, 26
T. Schwartzentruber, I. Boyd (2006)
A hybrid particle-continuum method applied to shock wavesJ. Comput. Phys., 215
Y. Sone (2007)
Molecular gas dynamics
D. Wadsworth, D. Erwin (1990)
One-dimensional hybrid continuum/particle simulation approach for rarefied hypersonic flows
Zhihui Li, Lin Bi, Hanxin Zhang, Lin Li (2011)
Gas-kinetic numerical study of complex flow problems covering various flow regimesComput. Math. Appl., 61
J-C Huang K Xu (2010)
A unified gas-kinetic scheme for continuum and rarefied flowsJ. Comput. Phys., 229
J. Burt, I. Boyd (2009)
A hybrid particle approach for continuum and rarefied flow simulationJ. Comput. Phys., 228
Chang Liu, K. Xu, Quanhua Sun, Q. Cai (2014)
A unified gas-kinetic scheme for continuum and rarefied flows,direct modeling,and full Boltzmann collision termarXiv: Numerical Analysis
G. Richard, J. Gerald, B. Ann (1996)
DSMC Grid Methodologies for Computing Low-Density, Hypersonic Flows About Reusable Launch Vehicles
Quanhua Sun, I. Boyd (2005)
Evaluation of Macroscopic Properties in the Direct Simulation Monte Carlo MethodJournal of Thermophysics and Heat Transfer, 19
C. Shen (2005)
Rarefied Gas Dynamics: Fundamentals, Simulations and Micro Flows
M. Ivanov, D. Khotyanovsky, A. Kudryavtsev, P. Vashchenkov, Gennady Markelov, A. Schmidt (2004)
Numerical Study of Backflow for Nozzle Plumes Expanding into Vacuum
J. Wu, Y. Lian, G. Cheng, R. Koomullil, K. Tseng (2006)
Development and verification of a coupled DSMC-NS scheme using unstructured meshJ. Comput. Phys., 219
Shanzhi Xu, Zi-niu Wu, Qian Li, Yan-ji Hong (2009)
Hybrid continuum/DSMC computation of rocket mode lightcraft flow in near space with high temperature and rarefaction effectComputers & Fluids, 38
Alejandro Garcia, J. Bell, W. Crutchfield, B. Alder (1999)
Adaptive Mesh and Algorithm Refinement Using Direct Simulation Monte CarloJournal of Computational Physics, 154
G. Bird (1994)
Molecular Gas Dynamics and the Direct Simulation of Gas Flows
Abstract A coupled NS-DSMC method possessing adapted-interface and two-way coupling features is studied to simulate the plume impingement effects of space thrusters. The continuum-rarefied interface is determined by combining KnGL and Ptne continuum breakdown parameters. State-based coupling scheme is adopted to transfer information between continuum and particle solvers, and an overlapping grid technique is investigated to combine structured-grid NS code and Cartesian-grid DSMC code to form the coupled solver. Flow problem of a conical thruster plume impinging on a cone surface is simulated using the coupled solver, and the simulation result is compared with experimental data, which proves the validity of the proposed method. Plume flow while the ascent stage of lunar module lifting off in lunar environment is also computed by using the present coupled NS-DSMC method to demonstrate its capability. The whole flow field from combustion chamber to the vacuum environment is obtained, and the result reveals that special attention should be paid to the plume aerodynamic force at the early stage of launching process.
Thermophysics and Aeromechanics – Springer Journals
Published: Nov 1, 2017
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