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...

A review of the state-of-the-art in hypersonic aeroelasticity and aerothermoelasticity is provided. Recently, the main focus in this area has been on the development of computational aeroelastic and aerothermoelastic methods capable of studying complete hypersonic vehicles. Thus, in addition to a survey of studies conducted in this area over the past six decades, two important issues are a focu...

Several different approaches to shape optimization are explored to identify hypersonic aeroshell shapes that will increase landed mass capability by maximizing drag-area for a specified lift-to-drag ratio. The most basic approach manipulates standard parameters associated with analytic aeroshell shapes like the sphere-cone and ellipsled. More general approaches manipulate the control points of ...

Hypersonic heating computations are still challenging due to difficulties in “A) robust capturing of shockwaves” and “B) accurate prediction of heating.” Based on our numerical survey for A), we found that the dissipation inside the numerical shock wave structure (where no physical or mathematical explanation is valid) must be proportional to Mach number, in contrast to Mach independent dissipa...

Hypersonic systems for space access and with strike capability are currently being researched by the Air Force. Flight testing and clearing them is particularly challenging, because of the speeds at which they operate. When anything unexpected occurs, the time to react is so short that the tested system must be destroyed. Therefore, the predictive analysis of these systems is essential for dete...

A numerical study employing discontinuous Galerkin method demonstrating net surface heat reduction for a cylindrical body in Mach 17 hypersonic flow is presented. This application focuses on using sinusoidal dielectric barrier discharge plasma actuators to inject momentum near the stagnation point. A 5 species finite rate air chemistry model completes the picture by analyzing the effect of the ...

A straightforward procedure has been developed to quickly determine an inviscid design of a hypersonic wind tunnel nozzle when the test gas is both calorically and thermally imperfect. This real gas procedure divides the nozzle into four distinct parts: subsonic, throat to conical, conical, and turning flow regions. The design process is greatly simplified by treating the imperfect gas effects ...