A simple model is presented for the analysis of inviscid flow fields over slender bodies accompanied by high rates of surface mass transfer. This model assumes a thin, inviscid injectant layer, which is separated from the outer flow by a contact discontinuity. Inviscid boundary-layer equations are shown to be applicable within the injectant layer, and the pressure gradient is found by matching ...

Experiments are performed in a Mach-6 shock tunnel to examine the laminar-to-turbulent transition process associated with sudden increase surface angle on slender body. A cone/flare geometry 5 $^\circ$ frustum and compression angles ranging from 15 allow range of mean flow configurations, spanning an attached shock-wave/boundary-layer interaction fully separated one; unit Reynolds number is als...

The stability of compressible plane Couette flow, which is a simple case of hypersonic wall-bounded shear flows, is not well understood even though incompressible Couette flow has been studied extensively by linear stability analysis and shown to be stable to linear disturbances. As a first step in studying the stability of three-dimensional hypersonic boundary layers, this paper studies the te...

The characterization of a hypersonic impulse facility is performed using variety methods including Pitot probe scans, particle image velocimetry, and schlieren imaging to verify properties such as the velocity, Mach number, wall boundary layer thickness, freestream turbulence intensity levels. experimental results are compared numerical simulations with Ansys Fluent compare design operational c...

This paper reviews work underway on the development of new technologies that will enhance the performance of hypersonic vehicles through plasma-related processes and the utilization of MHD to provide the large power levels that are required to drive these processes. Three technologies are discussed for plasma-enhanced hypersonic performance. These include: (1) the use of off-body plasmas for dr...

This study uses the non-intrusive generalized polynomial chaos method to investigate the effects of uncertainties in the gas-surface interaction model on the hypersonic boundary layer flow over a flat plate. In particular, the polynomial chaos method is applied to assess uncertainties in the surface shear, normal stress, heat flux, flowfield temperature and density resulting from uncertain surf...

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...