Redistribution of Energy during Interaction of a Shock Wave with a Temperature Layered Plasma Region at Hypersonic Speeds

O A Azarova,K V Krasnobaev,T A Lapushkina,O V Kravchenko

doi:10.3390/aerospace8110326

O A Azarova, K V Krasnobaev + Show 2 more

Open Access

https://doi.org/10.3390/aerospace8110326

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Abstract

The paper is devoted to the problem of the interaction between a shock wave and a thermally stratified energy source for the purpose of supersonic/hypersonic flow control realization. The effect of the thermally stratified energy source on a shock wave with the Mach number in the range of 6–12 is researched numerically based on the Navier-Stokes system of equations. Redistribution of specific internal energy and volume density of kinetic energy behind the wave front is investigated. Multiple manifestations of the Richtmyer-Meshkov instability has been obtained which has caused the blurring and disappearance of shock wave and contact discontinuity fronts in density fields. A study of the efficiency of using a stratified energy source instead of a homogeneous one with the same value of the full energy is carried out. The agreement with the available experimental data for the shock wave Mach number 6 has been obtained.

Highlights

The paper is devoted to the problem of the interaction between a shock wave and a thermally stratified energy source for the purpose of supersonic/hypersonic flow control realization
The effect of the thermally stratified energy source on a shock wave with the Mach number in the range of 6–12 is researched numerically based on the Navier-Stokes system of equations
The problems in the interaction of a shock wave with plasma structures can be considered as part of the direction of supersonic hypersonic flow control, since it simulates the interaction of energy sources with a bow shock wave created by an aerodynamic (AD) body in the flow

Summary

Introduction

The problems in the interaction of a shock wave with plasma structures can be considered as part of the direction of supersonic hypersonic flow control, since it simulates the interaction of energy sources with a bow shock wave created by an aerodynamic (AD) body in the flow. Leonov et al reviewed the plasma base methods for control of flow and shock wave configurations by the creation of different types of gas discharge near surfaces of AD bodies. Kourtzanidis et al investigated the plasma influence on bow shock wave configuration by means of gas discharge, created near the surface of AD body, and showed the possibility of influence to the shock position by plasma effects. In our works the possibility of the formation of flow regions behind the wave front with significantly increased values of the gas temperature due to the interaction of a thermally stratified energy source with the shock wave front has been shown [25]. The research can be important for achievement of high-speed flow control and improvement of the conditions for the processes of mixing and ignition in jets and combustion chambers

Numerical Method and Statement of the Problem

A Number of Working Nodes in the Calculation Area

Analysis of the Grid Convergence