Parallel Particle Simulation of the Near-Continuum Hypersonic Flows Over Compression Ramps-Reference-Cited by-同舟云学术

Parallel Particle Simulation of the Near-Continuum Hypersonic Flows Over Compression Ramps

Published:2003-01-01 Issue:1 Volume:125 Page:181-188
ISSN:0098-2202
Container-title:Journal of Fluids Engineering
language:en
Short-container-title:

Author:

Wu J.-S.¹,Tseng K.-C.¹

Affiliation:

1. Department of Mechanical Engineering, National Chiao-Tung University, 1001 Ta-Hsueh Road, Hsinchu 30050, Taiwan

Abstract

This paper describes the analysis of the near-continuum hypersonic flow over a compression ramp using the two-dimensional parallel direct simulation Monte Carlo (DSMC) method. Unstructured and triangular solution-based adaptive mesh depending on the local mean free path is used to improve the resolution of solution for the flow field with highly varying properties. In addition, a freestream parameter is defined to help reduced the cell numbers in the freestream area, resulting in appreciable decrease of the computational time (20–30%) without sacrificing the accuracy of the solution. The two-step multilevel graph partition technique is used for physical domain decomposition, employing estimated particle number distribution in each cell as the graph vertex weight. 32 IBM-SP2 processors are used throughout the study unless otherwise specified. The Effect of the outflow vacuum boundary condition, compression ramp angle, freestream condition, and length of the ramp to the flow field are investigated. Computational results are compared with previous numerical results whenever available.

Publisher

ASME International

Subject

Mechanical Engineering

Link

http://asmedigitalcollection.asme.org/fluidsengineering/article-pdf/125/1/181/5662961/181_1.pdf

Reference12 articles.

1. Anderson, J. D., Jr., 1989, Hypersonic and High Temperature Gas Dynamics, McGraw-Hill, New York.

2. Pullin, D. I., and Harvey, J. H., 1976, “A Numerical Simulation of the Rarefied Hypersonic Flat Plate Problem,” J. Fluid Mech., 78, pp. 689–707.

3. Vogenitz, F. W., Broadwell, J. E., and Bird, G. A., 1969, “Leading Edge Flow by the Monte Carlo Direct Simulation Technique,” 7th Aerospace Science Meeting, AIAA Paper No. 69–141.

4. Chun, C.-H., 1991, “Experiments on Separation at a Compression Corner in Rarefied Hypersonic Flow,” Rarefied Gas Dynamics, A. Beylich, ed., VCH Publishers, New York, pp. 562–569.

5. Moss, J., Rault, N., and Price, J. M., 1994, “Direct Monte Carlo Simulations of Hypersonic Viscous Interactions Including Separation,” Rarefied Gas Dynamics: Space Science and Engineering, B. D. Shzgal and D. P. Weave, eds., Washington, DC.

Cited by 7 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. High-speed rarefied gas flow simulations using Quasi-Gas Dynamic equations with slip and jump boundary conditions;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2022-05-27

2. Experimental Investigation of Hypersonic Laminar Flow Over a Compression Ramp;Journal of Fluids Engineering;2021-08-20

3. Development of parallel direct simulation Monte Carlo method using a cut-cell Cartesian grid on a single graphics processor;Computers & Fluids;2014-09

4. Modified gas-kinetic scheme for shock structures in argon;Progress in Computational Fluid Dynamics, An International Journal;2008

5. Gas-Kinetic Scheme for Continuum and Near-Continuum Hypersonic Flows;Journal of Spacecraft and Rockets;2007-11