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Медведев, А. Е.

doi:10.1023/a:1018811516116

Cited by 14 publications

(15 citation statements)

References 4 publications

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“…The relations connecting the pulsed energy release at the shock 3 j with its shape, changes in flow properties and stream deflection angles are given in [21][22][23][24][25]. In particular, according to [23], the flow turn angle 3 θ depends on the shock strength 3 J as it follows:…”

Section: Model and Methodsmentioning

confidence: 99%

Stationary Mach Configurations with Pulsed Energy Release on the Normal Shock

Чернышов

Kapralova

Матвеев

et al. 2021

Fluids

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We obtained a theoretical analysis of stationary Mach configurations of shock waves with a pulsed energy release at the main (normal) shock and a corresponding change in gas thermodynamic properties. As formation of the stationary Mach configuration corresponds to one of two basic, well-known criteria of regular/Mach shock reflection transition, we studied here how the possibility of pulsed energy release at the normal Mach stem shifts the von Neumann criterion, and how it correlates then with another transition criterion (the detachment one). The influence of a decrease in the “equilibrium” gas adiabatic index at the main shock on a shift of the solution domain was also investigated analytically and numerically. Using a standard detonation model for a normal shock in stationary Mach configuration, and ordinary Hugoniot relations for other oblique shocks, we estimated influence of pulsed energy release and real gas effects (expressed by decrease of gas adiabatic index) on shift of von Neumann criterion, and derived some analytical relations that describe those dependencies.

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Section: Model and Methodsmentioning

confidence: 99%

Stationary Mach Configurations with Pulsed Energy Release on the Normal Shock

Чернышов

Kapralova

Матвеев

et al. 2021

Fluids

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“…The jet temperature was proved in some studies to have no impact on the fore shock standoff distance [169] nor on drag [168]. Other studies [166,170] confirmed that increasing the jet total temperature yields more drag reduction which explains the relative superiority of plasma and high-temperature jets over conventional ones [166].…”

Section: Factors Controlling the Counterflow Effectivenessmentioning

confidence: 97%

“…Using a mixture of gases, the mixture ingredients were found to have a slight impact on jet function [126]. The higher effectiveness of lighter gases in reducing aeroheating and drag was explained owed to their higher specific kinetic energy that yields longer penetration for a given pressure ratio [166]. In the vicinity of stagnation and reattachment zones of the vehicle, heavier gases were found more effective in reducing aeroheating [134,164].…”

Section: Factors Controlling the Counterflow Effectivenessmentioning

confidence: 99%

“…This feature of plasma discharge (along with other energy discharge forms) will be discussed later in this survey. To date, the studies on opposing plasma jet have been exclusive to three research groups: Gordeev et al [166,170,210,213,214], Shang et al [152,215,216], and Fomin et al [217,218].…”

Section: Derivatives Of Opposing Jet Device 371 Opposing Plasma Jetsmentioning

confidence: 99%

“…These demands add to the design tradeoffs and degrade the overall efficiency [218,219]. Alternatively, light gases have shown results that are comparable to plasma jets at significantly lower stagnation temperatures [166,214] and can be considered as a proper solution.…”

Section: Derivatives Of Opposing Jet Device 371 Opposing Plasma Jetsmentioning

confidence: 99%

See 2 more Smart Citations

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Ahmed

Qin

2020

Progress in Aerospace Sciences

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One key feature that distinguishes the flowfield around vehicles flying in supersonic and hypersonic regimes is the bow shock wave ahead of forebody. The severe drag and aeroheating impacting these vehicles can be significantly reduced if the bow shock wave ahead of the vehicles forebodies is controlled to yield weaker system of oblique shocks. Benefits of forebody shock control include increasing flight ranges, economizing fuel consumption, reducing dead weights, and thermally protecting forebody structure and onboard equipment. Forebody shock control that has been widely studied since the early 1900s is achievable in numerous techniques that vary according to the mechanism of control. While some of these techniques have already been implemented in real systems, other techniques involve serious complications and tough trade-offs. The present paper is intended to serve as the first comprehensive survey on the field of forebody shock control devices. The objectives of the present paper are multifold. The paper categorizes the various forebody shock control devices in a physics-based manner, explains the underlying physics for each device, and surveys the key studies and state-of-the-art knowledge. The paper also addresses the existing gaps in knowledge, highlights the existing systems implementing these devices, and discusses the associated practical implementation issues and design-tradeoffs. 2. Structural devices, the mechanical spikes: 2.1. Principle of operation of mechanical spikes Drag and Aeroheating Reduction Devices Fluidic Devices Opposing jets Structural Devices Mechanical spikes Energetic Devices Energy deposition Basic devices Structural-Fluidic Devices Structural-Energetic Devices Hybrid devices

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Existence of self-similar solutions in reacting gases

Jena

Singh

2014

Shock Waves

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Untitled

Cited by 14 publications

References 4 publications

Stationary Mach Configurations with Pulsed Energy Release on the Normal Shock

Stationary Mach Configurations with Pulsed Energy Release on the Normal Shock

Forebody shock control devices for drag and aero-heating reduction: A comprehensive survey with a practical perspective

Existence of self-similar solutions in reacting gases

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