This paper presents a study of the breakdown of the Navier–Stokes equations in hypersonic viscous flows over a sharp cone tip and a hollow cylinder/flare geometry. Investigations are performed through detailed comparisons of the numerical results obtained with continuum and particle techniques. The objective of the study is to predict conditions under which the continuum approach may be expecte...

A theoretical study is made of hypersonic flows over thin bodies subject to the combined effect of leading-edge bluntness^, boundary-layer displacement as well as surface incidence,, Within the scope of the boundary-layer theory and the hypersonic small-disturbance theorys an approach is developed based on a flow model consisting of three adjoining regionss an inner laminar boundary layerj an o...

There has been little research into surface-ablation effects on hypersonic boundary-layer instability, and the current understanding of real-gas effects on hypersonic boundary-layer instability still contains uncertainties. The objective of the current work was to analyze the hypersonic boundary-layer transition process using linear-stability theory, inwhich surface ablation, aswell as real-gas...

There have been many studies of turbulent combustion flows, however the interaction between turbulent motion and the chemical reactions that occur in hypersonic flows has not been studied. In these flows, the rate of product formation depends almost exclusively on the temperature, and small temperature fluctuations may produce large changes in the rate of product formation. To study this proces...

A new method is offered to simulate heat transfer processes in nonequilibrium viscous shock layers near the catalytic body surface at hypcrsonic wind tunnel and free natural flight conditions. The method is based on computations of nonequilibrium parameters in thin viscous sbock layers, and on an analogy with flows that arise behind normal shock waves. The obtained simplified relationships betw...

We investigate the leading-edge separation, also called negligible boundary-layer thickness induced by an impinging shock on a sharp flat plate. The canonical wave/boundary-layer interaction configuration consisting of wedge and plate wall, placed in hypersonic free stream, is used for investigations. first construct theoretical model separated flow field (LESF) which predicts separation bubble...

This paper presents explicit analytical solutions of the pressure coefficient and the pressure ratio across the oblique shock and expansion waves in function of the flow deflection angle. These new explicit pressure-deflection solutions can be efficiently used in solving applied aerodynamic problems in supersonic flows, such as the aerodynamics of airfoils and wings in supersonic-hypersonic flo...

In this paper, the relation between skin friction and heat transfer along windward sides of blunt-nosed bodies in hypersonic flows is investigated. The self-similar boundary layer analysis is accepted to figure out the distribution of the ratio of skin friction to heat transfer coefficients along the wall. It is theoretically obtained that the ratio depends linearly on the local slope angle of ...

Application of the newly emerged space-time conservation element solution element (CESE) method to compressible Navier-Stokes equations is studied. In contrast to Euler equations solvers, several issues such as boundary conditions, numerical dissipation, and grid stiffness warrant systematic investigations and validations. Non-reflecting boundary conditions applied at the truncated boundary are...