Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme

The gas-kinetic Bhatnagar–Gross–Krook (BGK) scheme is extended to hypersonic ﬂow simulations and thus shows that the compressible inviscid ﬂow solutions of the simulations are efﬁciently and accurately obtained from the BGK scheme without the disastrous shock instability phenomenon that occurs in...

Full description

Bibliographic Details
Main Authors:	Chit, O.J., Omar, Ashraf Ali, Asrar, Waqar, Zaludin, Z. A.
Format:	Article
Language:	English
Published:	The American Institute of Aeronautics and Astronautics (AIAA) 2005
Subjects:	TL500 Aeronautics
Online Access:	http://irep.iium.edu.my/5934/ http://irep.iium.edu.my/5934/ http://irep.iium.edu.my/5934/4/waqar_1.11174.fp.pdf

id	iium-5934
recordtype	eprints
spelling	iium-59342013-08-27T03:42:54Z http://irep.iium.edu.my/5934/ Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme Chit, O.J. Omar, Ashraf Ali Asrar, Waqar Zaludin, Z. A. TL500 Aeronautics The gas-kinetic Bhatnagar–Gross–Krook (BGK) scheme is extended to hypersonic ﬂow simulations and thus shows that the compressible inviscid ﬂow solutions of the simulations are efﬁciently and accurately obtained from the BGK scheme without the disastrous shock instability phenomenon that occurs in most hypersonic ﬂow simulations involving strong shock waves. For this particular study, the effect of chemistry in hypersonic ﬂows has not been taken into account. Hence, the assumption of calorically perfect gas is imposed in all simulations. The high-order resolution of the scheme is achieved by utilizing monotone upstream-centered schemes for conservation laws-type initial reconstruction. While, an implicit-type time-integration method known as the approximate factorization– alternating direction implicit is adopted for computing both steady and unsteady calculations. The gas-kinetic scheme is tested meticulously in four two-dimensional numerical examples, namely, the blunt-body problem, the double Mach reﬂection problem, the axisymmetric blunt-body problem, and the ﬂow over a 15-deg ramp. The numerical results of the BGK scheme when compared with the other schemes and experimental data show that this numerical technique is robust, accurate, and stable for hypersonic ﬂow. The American Institute of Aeronautics and Astronautics (AIAA) 2005-07 Article PeerReviewed application/pdf en http://irep.iium.edu.my/5934/4/waqar_1.11174.fp.pdf Chit, O.J. and Omar, Ashraf Ali and Asrar, Waqar and Zaludin, Z. A. (2005) Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme. AIAA JOURNAL, 43 (7). pp. 1427-1433. ISSN 0001-1452 doi: 10.2514/1.11174
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL500 Aeronautics
spellingShingle	TL500 Aeronautics Chit, O.J. Omar, Ashraf Ali Asrar, Waqar Zaludin, Z. A. Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme
description	The gas-kinetic Bhatnagar–Gross–Krook (BGK) scheme is extended to hypersonic ﬂow simulations and thus shows that the compressible inviscid ﬂow solutions of the simulations are efﬁciently and accurately obtained from the BGK scheme without the disastrous shock instability phenomenon that occurs in most hypersonic ﬂow simulations involving strong shock waves. For this particular study, the effect of chemistry in hypersonic ﬂows has not been taken into account. Hence, the assumption of calorically perfect gas is imposed in all simulations. The high-order resolution of the scheme is achieved by utilizing monotone upstream-centered schemes for conservation laws-type initial reconstruction. While, an implicit-type time-integration method known as the approximate factorization– alternating direction implicit is adopted for computing both steady and unsteady calculations. The gas-kinetic scheme is tested meticulously in four two-dimensional numerical examples, namely, the blunt-body problem, the double Mach reﬂection problem, the axisymmetric blunt-body problem, and the ﬂow over a 15-deg ramp. The numerical results of the BGK scheme when compared with the other schemes and experimental data show that this numerical technique is robust, accurate, and stable for hypersonic ﬂow.
format	Article
author	Chit, O.J. Omar, Ashraf Ali Asrar, Waqar Zaludin, Z. A.
author_facet	Chit, O.J. Omar, Ashraf Ali Asrar, Waqar Zaludin, Z. A.
author_sort	Chit, O.J.
title	Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme
title_short	Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme
title_full	Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme
title_fullStr	Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme
title_full_unstemmed	Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme
title_sort	hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme
publisher	The American Institute of Aeronautics and Astronautics (AIAA)
publishDate	2005
url	http://irep.iium.edu.my/5934/ http://irep.iium.edu.my/5934/ http://irep.iium.edu.my/5934/4/waqar_1.11174.fp.pdf
first_indexed	2023-09-18T20:14:45Z
last_indexed	2023-09-18T20:14:45Z
_version_	1777407712599998464

Hypersonic flow simulation by the gas-kinetic bhatnagar-gross-krook scheme

Similar Items