Shock-Wave Structure of Supersonic Jet Flows

Valery Zapryagaev,Nikolay Kiselev,Dmitry Gubanov

doi:10.3390/aerospace5020060

Abstract

In the present paper, we give a brief overview of the studies of supersonic jet flows which were performed recently with the aim of gaining experimental data on the formation of the shock-wave structure and jet mixing layer in such flows. Considerable attention is paid to a detailed description of discharge conditions for supersonic jets, to enable the use of measured data for making a comparison with numerical calculations. Data on the 3D flow structure in the mixing layer of the initial length of a supersonic jet are reported. Scientific interest in this phenomenon is due to its practical significance in studying the possibility of intensifying the mixing process as well as in studying the sound-generation process.

Highlights

The necessity to study supersonic gas jets arises, first, due to the wide use of such flows in various technological apparatuses and, second, due to the high level of force, thermal, and pulsating loads generated when such supersonic flows impinge onto obstacles
The experimentally obtained contour lines of total pressures measured in various cross-sections of a jet emanating from a nozzle provided with chevrons are shown in Figure 7; here, results of numerical calculations comply with the experimental data of Reference [40]
This review presents the results of investigations on supersonic jet flows that have been carried out in the Laboratory of Experimental AeroGasDynamics of the Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch of the Russian Academy of Sciences

Summary

Introduction

The necessity to study supersonic gas jets arises, first, due to the wide use of such flows in various technological apparatuses and, second, due to the high level of force, thermal, and pulsating loads generated when such supersonic flows impinge onto obstacles. Activities aimed at the development of new-generation, future technology-manned transportation vehicles using a reentry system that includes a multijet system necessary for deceleration near the landing surface are under way, Figure 1 [28] The application of such a multijet system necessitates the study of the detailed shock-wave structure of the flow in free high-pressure supersonic jets and in jets impinging onto the surface under landing conditions. Difficulties in the study of physical mechanisms within the indicated activities consist in the existence of a multitude of fundamental points to be taken into consideration Among such points are problems in the hydrodynamic instability of supersonic shear flows (boundary layer and mixing layer), the development of small perturbations and their interaction with compression shocks, the mechanisms of acoustic emission by high-speed flows, the emergence of self-oscillations, and the shock-wave structure of supersonic non-isobaric jets. Siberian Branch of the Russian Academy of Science, ITAM SB RAS) (b) [28]

Spatial Structure in the Jet Shear Layer of a Supersonic Underexpanded Jet

Conclusions