Physico - Chemical Modelling in Nonequilibrium Hypersonic Flow Around Blunt Bodies

Tchuen, Ghislain; Burtschell, Yves

doi:10.5772/18941

Cited by 7 publications

(1 citation statement)

References 34 publications

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“…where the primitive and conservative vectors are expressed as: Table.1. The above air reaction model can be referred to [6]. Table.1 High-temperature reaction model of Air…”

Section: The Flow Mechansim In the Hypersonic Interaction Regionmentioning

confidence: 99%

The Mechanism of Three-Dimension Steady Shock Wave Interaction

Chun

Yang

Jiang

2018

Volume 1: Flow Manipulation and Active Control; Bio-Inspired Fluid Mechanics; Boundary Layer and High-Speed Flows; Fluids Engin

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The problem of three-dimensional steady shock wave interaction is a key issue for supersonic and hypersonic corner flow. Due to the complexity of shock configurations, there is no analytical theory to such problem and the mechanism of three-dimensional shock waves and boundary layer interaction has not been clearly known. In this paper, an analytical approach to the problem of three-dimensional steady shock wave interaction was exhibited to analytically interpret the mechanism of three-dimensional interaction of two oblique planar shock waves. The results showed that the problem of three-dimensional steady shock wave interaction could be transformed to that of two moving shock wave interaction in two-dimensional plane, and there are various interaction configurations such as regular interaction, Mach interaction and weak interaction. The mechanism of three-dimensional shock wave interaction is helpful to understand the complex flow mechanism induced by three-dimensional shock wave and boundary layer in hypersonic flow. The interaction of three-dimensional shock waves and boundary layer plays important role in the complex flow feature in hypersonic rudder region. The contact surface induced by three-dimensional shock waves represents a local jet. When the flow jet impinges on the boundary layer of wall surface, the jet makes the boundary layer thinner and will inevitably cause local heat flux peak. The interaction configurations of three-dimensional shock wave play important role in the gasdynamic heating mechanisms of hypersonic complex flow.

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“…where the primitive and conservative vectors are expressed as: Table.1. The above air reaction model can be referred to [6]. Table.1 High-temperature reaction model of Air…”

Section: The Flow Mechansim In the Hypersonic Interaction Regionmentioning

confidence: 99%

The Mechanism of Three-Dimension Steady Shock Wave Interaction

Chun

Yang

Jiang

2018

Volume 1: Flow Manipulation and Active Control; Bio-Inspired Fluid Mechanics; Boundary Layer and High-Speed Flows; Fluids Engin

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Multi-GPU unsteady 2D flow simulation coupled with a state-to-state chemical kinetics

Tuttafesta¹,

Pascazio

Colonna

2016

Computer Physics Communications

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MHD heat flux mitigation in hypersonic flow around a blunt body with ablating surface

Bityurin¹,

Bocharov²

2018

J. Phys. D: Appl. Phys.

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One of the possible applications of magnetohydrodynamic flow control is considered. Namely, the surface heat flux mitigation by means of magnetohydrodynamic (MHD) interaction in hypersonic flow around a blunt body. The 2D computational model realizes a coupled solution of chemically non-equilibrium ionized airflow in magnetic field. Heat- and mass-transfer due to the ablation of materials from the body surface is taken into account. Two cases of free-stream flow conditions are considered: moderate free-stream velocity (7500 m s−1) case and high free-stream velocity (11 000 m s−1) case. It is shown that the first flow case results in moderate ionization in the shock layer, while the second flow case results in high ionization. In the first case, the Hall effect is significant, and effective electrical conductivity in the shock layer is rather low. In the second case, the Hall effect reduces, and effective conductivity is high. Even if the Hall effect is strong, as in the first case, intensive MHD deceleration of the flow behind the shock is provided due to the presence of insulating boundaries, the bow shock front and non-conductive wall of the blunt body. In the second case, high effective conductivity provides a high intensity of MHD flow deceleration. In both cases, a strong effect of MHD interaction on the flow structure is observed. As a consequence, a noticeable reduction of the surface heat flux is revealed for reasonable values of magnetic induction. The new treatment of mechanism for the surface heat flux reduction is proposed, which is different from commonly used one assuming that MHD interaction increases the bow shock stand-off distance, and, consequently results in a decrease of the mean temperature drop across the shock layer. The new effect of ‘saturation of heat flux’ is discussed.

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Physico - Chemical Modelling in Nonequilibrium Hypersonic Flow Around Blunt Bodies

Cited by 7 publications

References 34 publications

The Mechanism of Three-Dimension Steady Shock Wave Interaction

The Mechanism of Three-Dimension Steady Shock Wave Interaction

Multi-GPU unsteady 2D flow simulation coupled with a state-to-state chemical kinetics

MHD heat flux mitigation in hypersonic flow around a blunt body with ablating surface

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