Acomputational study is carried out to develop a fully implicit and time-accuratecomputational e uid dynamics code for the analysis of reactive e ow systems. Periodically oscillating shock-induced combustion around a blunt body in a stoichiometric hydrogen ‐air mixture is used as a validation problem of examining various numerical considerations. Euler equations and species conservation equations are used as the governing equations for the chemically reacting e ow. Spatial discretization of the governing equation is based on Roe’ s approximate Riemann solver with a MUSCL-type total variation diminishing scheme for higher-order spatial resolution. The secondorder-accuratetimeintegrationmethodisbasedonalower ‐uppersymmetricGauss ‐Seidelscheme,usingaNewton subiteration method and Steger ‐Warming e ux Jacobian splitting. As a e rst step of the validation procedure, simulations of experimental results were carried out to cone rm the reliability of the baseline method. In the next step, the general aspects of the baseline method were examined, including order of time integration, number of subiterations, and use of approximate e ux Jacobian splitting. Appropriateness of the grid system is also examined by using a grid ree nement study.

Computational Fluid Dynamics Algorithms for Unsteady Shock-Induced Combustion, Part 1: Validation

A new approach of a limiting process for multi-dimensional flows

The aim of the present work is to carry out Reynolds-averaged Navier-Stokes computations of flow through the inlet of a hypersonic research vehicle with a view to accomplish detailed aerodynamic analysis Three inlet configurations that differ in the inlet-duct height are considered in this study The results of this study are13; presented in the form of detailed computational flow visualization through density contours, variation of flow parameters at various desired sections, and inlet performance in each case

Computational Analysis of Inlet Aerodynamics for a Hypersonic Research Vehicle

During reentry and hypersonic igh t of space vehicles through atmosphere real gas eects come into play. The analysis of such hypersonic o ws is critical for proper aerothermal design of these vehicles. The present work emphasises numerical simulation of hypersonic o w with chemical non-equilibrium. A Reynolds Averaged Navier-Stokes code has been developed for this purpose employing an improved Roe scheme which is very robust and does not require any entropy x. To the best knowledge of the authors, such a formulation for real gas o w has not been reported earlier. A circular cylinder test case for which experimental data is available has been used to validate the code. Nomenclature _ !s mass rate of production of the species s s molar concentration of species s coecien t of thermal conductivity s thermal conductivity of the species s i

An Improved Roe Scheme for Real Gas Flows

Implementation and testing of Spalart-Allmaras model in a multi-block code

This paper discusses some aspects of three-dimensional supersonic and hypersonic inviscid blunt body flow computations. The method used is based on the solution of the Euler equations employing an explicit, upwind total variation diminishing formulation of the Roe Riemann solver within the cell-centered finite volume approach. A comparative study of various total variation diminishing limiters and entropy fixes is carried out to identify the most appropriate combination. The effect of using cell spacing in the total variation diminishing extrapolations is highlighted. Furthermore, a Mach number dependence and grid sensitivity study is carried out on various total variation diminishing limiters scaled with mesh spacing. Local time stepping and code parallelization has been employed to accelerate convergence in terms of effective wall clock times.

K. Ravi

Papers

Some aspects of high-speed blunt body flow computations with Roe scheme