Computational Fluid Dynamics in Hypersonic Aerothermodynamics

Krishnendu Sinha

doi:10.14429/dsj.60.604

Krishnendu Sinha Indian Institute of Technology Bombay, Mumbai

DOI: https://doi.org/10.14429/dsj.60.604

Keywords: Hypersonic aerothermadynamics, computational fluid dynamics, scramjet engine, hypersonic flows, scramjet inlet, re-entry capsules

Abstract

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

Author Biography

Krishnendu Sinha, Indian Institute of Technology Bombay, Mumbai

Dr Krishnendu Sinha received his BTech (Aerospace Engineering) from the Indian Institute of Technology Kanpur in 1995. He received his Masters and PhD in Aerospace Engineering from the University of Minnesota, USA. He joined Indian Institute of Technology Bombay, Mumbai as Assistant Professor in 2006. Since then, he has focused on the modelling and simulation of high-speed flows. His research interests and expertise are in the areas of computational fluid dynamics, turbulence modelling and hypersonic flow simulation.