Rarefied gas phenomena are found in a wide variety of hypersonic flow applications, and accurate characterization of such phenomena is often desired for engineering design and analysis. In atmospheric flows involving high Mach numbers and/or low densities, underlying assumptions in a continuum fluid dynamics description tend to break down, and distributions of both molecule velocity and interna...

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...

Wind tunnels are being used to study the aerodynamic properties of race cars, fighter planes etc. It allows us to make a reusable prototype and test it in the tunnel. Hypersonic wind tunnels operate at hypersonic speeds ie, with a mach number greater than 6. For doing experiments, it is necessary to maintain a constant pressure in the settling chamber of the tunnel so that we get the desired Ma...

This paper is devoted to predict laminar and turbulent heating rates around blunt re-entry spacecraft at hypersonic conditions. Heating calculation of a hypersonic body is normally performed during the critical part of its flight trajectory. The procedure is of an inverse method, where a shock wave is assumed, and the body shape that supports this shock, as well as the flowfield between the sho...

Hypersonic airbreathing vehicles are characterized by highly-integrated airframe and propulsion system. Computational Fluid Dynamics (CFD) tools have been used extensively in the design and analysis phrase of hypersonic vehicles. In this paper, an engineering method and a finite volume method based on the center of grid are developed for preliminary research of interested integrative hypersonic...

A parallel computational fluid dynamics code has been developed for the study of aerodynamic heating problem in hypersonic flows. The code employs the 3D Navier-Stokes equations as the basic governing equations to simulate the laminar hypersonic flow. The cell centered finite volume method based on structured grid is applied for spatial discretization. The AUSMPW+ scheme is used for the invisci...

Wind tunnel is a test facility used to simulate the flight conditions. It allows us to make a reusable prototype and test it in the tunnel in low cost. Hypersonic wind tunnels operate at hypersonic speeds ie, with a mach number greater than 6. For doing experiments, it is necessary to maintain a constant pressure in the settling chamber of the tunnel so that we get the desired mach number and m...

Hypersonic chemically reacting flow around a wedge in the near-continuum regime was numerically studied by the DSMC method with the main goal of validation of real gas effect models. The influence of vibration-dissociation coupling on the results of numerical simulations was analyzed. To this end, two models of chemical reactions were used in the computations, the total collisional energy model...

The flow topologies of gas and liquid injection into hypersonic crossflow are compared with the flow topology around 3D rigid obstacles in hypersonic flow. Experimental techniques such as oil flow visualization, infrared thermography, sublimation technique and high speed Schlieren photography are applied for a Mach 6 crossing flow on a flat plate. The shock system and the vortex system are visu...

Passive control of hypersonic boundary-layer transition using porous coatings has been studied by theoretical analyses, experiments, and numerical simulations. It was found that porous coating stabilizes Mack’s second mode and destabilizes Mack’s first mode. However, there are only few studies on the stabilization efficiency of porous coating. And no work has been reported about the thermochemi...