Computational Fluid Dynamics in Hypersonic Aerothermodynamics

Defence Science Journal

Krishnendu Sinha¹ 

[1] Indian Institute of Technology Bombay, Mumbai

关键词: Hypersonic aerothermadynamics;    computational fluid dynamics;    scramjet engine;    hypersonic flows;    scramjet inlet;    re-entry capsules;   

DOI  :  

学科分类：社会科学、人文和艺术（综合）

来源: Defence Scientific Information & Documentation Centre

【 摘 要 】

Hypersonic flows are characterised by high Mach number and high total enthalpy. An elevated temperature often results in thermo-chemical reactions in the gas, which p lay a major role in aerothermodynamic characterisation of high-speed aerospace vehicles. Hypersonic flows in propulsion components are usually turbulent, resulting in additional effects. Computational simulation of such flows, therefore, need to account for a range of physical phenomena. Further, the numerical challenges involved in resolving strong gradients and discontinuities add to the complexity of computational fluid dynamics (CFD) simulation. In this article, physical modelling and numerical methodology-related issues involved in hypersonic flow simulation are highlighted. State-of-the-art CFD challenges are discussed in the context of two prominent applications-the flow in a scramjet inlet and the flow field around a re-entry capsule. Defence Science Journal, 2010, 60(6), pp.663-671 , DOI:http://dx.doi.org/10.14429/dsj.60.604

【 授权许可】

Unknown