Control of the Shape and Position of a Bow Shock Wave, Drag and Lift Forces, and Self-Sustained Flow Pulsations Using Stratified Energy Supply |Chapter 8 | Physical Science: New Insights and Developments Vol. 3

 

In this study, a method for controlling high-speed flows using a continuously acting thermally stratified energy deposition is presented. The study analyses the dependence of the shape and position of a bow shock wave, drag and lift forces, and self-sustained flow pulsations on the temperature values ​​in the layers of a stratified energy source acting on an aerodynamic body. Numerical modelling is based on the system of the Navier-Stokes equations for viscous heat-conducting gas (air) at freestream Mach number M∞=2. A detailed visualisation of the dynamics of the density, pressure, temperature, and local Mach number fields during the controlled establishment of steady-state flow regimes is presented. Multiple manifestation of the Richtmyer–Meshkov instability is demonstrated. Sharp peaks accompanying the development of Richtmyer–Meshkov instabilities are observed. These peaks persist even in the steady-state flow regime established under the action of stratified energy supply, changing the shape of the bow shock wave and giving it a wavy form. Basic approaches to controlling the shape and position of the bow shock wave, drag, and lift (pitch) forces (at zero angle of attack), as well as stability in steady-state supersonic flow past an aerodynamic body, have been developed using a continuously operating thermally stratified energy deposition. The possibility of generating and damping self-sustaining flow pulsations, as well as the formation of a steady flow with opposing, continuously acting lift forces, is demonstrated by changing the temperature in the layers of the thermally stratified energy source. The practical application of the developed methods for control of the characteristics and stability of high-speed flow/flight can be associated with the development of non-mechanical control systems for aircraft at the stage of echelon (horizontal) flight.

 

Author(s) Details

 

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

 

Please see the book here :- https://doi.org/10.9734/bpi/psniad/v3/6675

 

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