Impact of Thermally Stratified Plasma Region on Redistribution of Energy behind a Shock Wave Front at Hypersonic Speeds | Chapter 4 | New Frontiers in Physical Science Research Vol. 8

 The question of the interaction of a shock wave accompanying different strength structures lies in the prevailing of the scientific course of supersonic/hypersonic flow control. This Chapter considers the effect of a thermally layered high strength region on a shock wave accompanying a Mach number in the range of 6-12. The redistribution of specific within energy and of the volume mass of kinetic energy behind the wave front is intentional. The blurring and disappearance of sudden strong wave fronts in density fields was acquired due to the multiple exhibition of the Richtmyer-Meshkov instability all the while the interaction of a thermally stratified strength source accompanying a shock wave. The effectiveness of utilizing a stratified beginning rather than a homogenous one accompanying the same filled energy value is examined. There is agreement accompanying the experimental evidence that is now accessible.

Author(s) Details:

O. A. Azarova,
Federal Research Center “Computer Science and Control” of the Russian Academy of Sciences, Vavilova st. 40, 119333, Moscow, Russian Federation.

T. A. Lapushkina,
Ioffe Institute, Politekhnicheskaya str. 26, 194021, St Petersburg, Russian Federation.

K. V. Krasnobaev,
Lomonosov Moscow State University, Faculty of Mechanics and Mathematics, Leninskiye Gory, Main Building, 119991, GSP-1, Moscow, Russian Federation.

O. V. Kravchenko,
Federal Research Center “Computer Science and Control” of the Russian Academy of Sciences, Vavilova st. 40, 119333, Moscow, Russian Federation.

Please see the link here: https://stm.bookpi.org/NFPSR-V8/article/view/9686

Dynamics of Shock Structure and Frontal Drag Force in a Supersonic Flow Past a Blunt Cone under the Action of Plasma Formation: A Recent Study | Chapter 4 | Current Overview on Science and Technology Research Vol. 4

 The impact of a plasma generation on the supersonic flow through a body called a "blunt cone-cylinder" is investigated experimentally and via computational fluid dynamics (CFD) in this chapter. A sequence of Schlieren images of the non-stationary interaction between the bow shock wave and blast wave are obtained using high speed shadowgraphy. The Euler equation system serves as the foundation for the calculations that follow. The freestream has a Mach number of 3.1. A bounded gas volume with increased pressure undergoes an immediate energy explosion to depict the plasmoid. It has been investigated how a bow shock wave and blast flow interact to generate a shock wave structure. The enormous energy released to a supersonic flow (500J) enabled the production of a schematic illustrating the origin and dynamics of the succeeding shock waves and contact discontinuities, as well as a significant reduction in drag force and stagnation pressure (close to 80%). A low density and high gas temperature zone, which is the main element lowering frontal body drag force, was also studied in terms of its dynamics. For various plasmoid energy values, the dynamics of the front surface drag forces have been examined. The computational and experimental flow patterns were found to be qualitatively in agreement.

Author(s) Details:

Irina Znamenskaya,
Lomonosov Moscow State University, 119234, Leninskie Gory 1, Build 2, Moscow, Russia.

Vladimir Chernikov,
Lomonosov Moscow State University, 119234, Leninskie Gory 1, Build 2, Moscow, Russia.

Olga Azarova,
Federal Research Center, “Computer Science and Control” of the Russian Academy of Sciences, 119333, Vavilova Street 44, Moscow, Russia.

Please see the link here: https://stm.bookpi.org/COSTR-V4/article/view/8282