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...

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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:
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
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Summary: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.