in the present work, an engineering method is developed to predict laminar and turbulent heating-rate solutions for blunt reentry spacecraft at hypersonic conditions. the calculation of aerodynamic heating around blunt bodies requires alternative solution of inviscid flow field around the hypersonic bodies. in this paper, the procedure is of an inverse nature, that is, a shock wave is assumed a...

Abstract—Hypersonic flows around spatial vehicles during their reentry phase in planetary atmospheres are characterized by intense aerothermodynamics phenomena. The aim of this work is to analyze high temperature flows around an axisymmetric blunt body taking into account chemical and vibrational non-equilibrium for air mixture species and the no slip condition at the wall. For this purpose, th...

This report describes how using the Navier-Stokes equations to numerically calculate a shock wave will more accurately depict a realistic and observed shock wave. Earlier related inviscid shock capturing studies that have attempted to numerically calculate the shock wave and downstream field surrounding a blunt body re-entering the atmosphere have exhibited an instability known as the carbuncle...

A numerical study is performed to simulate the cavitating flow, evaluating applicability of different flow fluctuation pressure (FFP) models such as Singhai FFT model, modified Singhal shear strain and present strain-vorticity model. The axisymmetric blunt-body with availability experimental data selected for simulation purpose. According results, first three FFP produce nearly similar coeffici...

Hypersonic flows around spatial vehicles during their reentry phase in planetary atmospheres are characterized by intense aerothermal phenomena. The aim of this work is to analyze high temperature flows around an axisymmetric blunt body taking into account chemical and vibrational non-equilibrium for air mixture species. For this purpose, a finite volume methodology is employed to determine the...

The numerical simulation of the three-dimensional flow upwind of a vertical cylinder over a flat plate is achieved with a parallel LES code which is called DNSUTA Version III. The preliminary computational results with a coarse grid find that the flow structure is similar to experimental observations. The bow shock is very clear, and a separation shock is formed ( Λ -structure). Inside the sepa...