The character of the boundary layer noise and ambient tunnel noise are of interest in the experimental study of laminar to turbulent transition. The instability mechanism in hypersonic flow over slender bodies is the acoustic mode. A number of investigations of flow over a slender cone in high-enthalpy facilities have been performed; however, measurements of the boundary layer noise and ambient...

A method for computing inviscid hypersonic ow over complex con gurations using unstructuredmeshes is presented. The unstructured grid solver uses an edge{based nite{volume formulation. Fluxes are computed using a ux vector splitting scheme that is capable of representing constant enthalpy solutions. Second{order accuracy in smooth ow regions is obtained by linearly reconstructing the solution, ...

In hypersonic flow computations, it is a key issue to predict surface heating accurately, though this is still challenging because there always are possibilities of resulting in anomalous solutions. In this paper, three properties for flux functions are proposed: 1) shock stability/robustness, 2) conservation of total enthalpy, and 3) resolving boundary layer. Then, numerical experiments are pe...

A novel parameterized model for temperature distribution is proposed. A framework for uncertainty quantification and global sensitivity in hypersonic aerothermoelastic analysis is developed based on this model. The uncertainty quantification and global sensitivity analysis in hypersonic aerothermoelastic analysis for control surface due to hypersonic aerothermodynamics is investigated in this s...

The paper deals with the formulation of a consistent set of governing equations apt to describe the physical phenomenology comprising the hypersonic flow field of an ionized gas mixture and the electromagnetic field. The governing equations of the flow field and those of the electromagnetic field are revisited in sequence and differences or similarities with past treatments are pointed out and ...

Shock/boundary layer interaction (SBLI) is an undesirable phenomenon, occurring in high-speed propulsion systems. The conventional method to manipulate and control SBLI is using a bleed system that involves the removal of a certain amount of mass of the inlet flow to control boundary layer separation. However, the system requires a larger nacelle to compensate the mass loss, larger nacelles con...

For aerospace or hypersonic cruise vehicle the state of the boundary layer is of great importance because for turbulent boundary layers, the thermal loads and skin friction are higher than in laminar boundary layers. Therefore , knowledge of cooling features and laminar-turbulent transition is necessary for the design of the thermal protection system (TPS). Different strategies are used to redu...

This paper applies the high-order finite-volume essentially nonoscillatory (ENO) schemes to unsteady hypersonic shock-shock interference heating on a circular cylinder. Compared with most of the current second-order numerical methods, which usually are not uniformly accurate, the EN0 schemes are able to achieve uniformly high-order accuracy with essentially no oscillation in simulating the aero...