An investigation of tailored upstream heating for sonic boom and drag reduction

Marconi, F.

doi:10.2514/6.1998-333

Cited by 26 publications

(10 citation statements)

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“…The interaction time t is counted from the moment when the shock and the interface first meet each other. This system of equations (16)(17)(18)(19), together with the equations (2-10) have been used to simulate the data for the vorticity generation. Figs.…”

Section: C Power-law Density Distribution Casementioning

confidence: 99%

“…The complex nature and a number of co-processes often involved in this type of the interaction can be seen from the images of the initially simply structured planar, bow, or oblique shock evolving into a complicated system of distorted and secondary shocks with flow separation regions and formation of vortices [12]. Among the most remarkable changes are: the shock wave acceleration and its strong front distortion increasing with time followed with remarkable weakening of the shock until it appears less and less identifiable [12][13][14][15]; motion of the shock away from the body in the presence of heating [16]; substantial changes in the gas/plasma parameter distribution behind the shock, particularly sharp reduction of pressure [17]; remarkable, up to 40% reduction in the wave drag experienced by a body when the plasma is created upstream [18,19]; the time-delays in the effects on the flow relative to the discharge on-off times and a finite pressure rise time [7]; and a vortex system formation in the flow behind the shock often followed with strong distortion or collapse of the plasma region [4,7].…”

Section: Introductionmentioning

confidence: 99%

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A mechanism of vortex generation in a supersonic flow behind a gas-plasma interface

Markhotok

2018

Fluid Dyn. Res.

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The origin of a vortex structure generated during the shock-plasma interaction is investigated. A two-dimensional model based on the shock refraction mechanism successfully unifies the vortex generation with major co-processes typical for the interaction and thus well fits in their cause-and-consequence relationship. Numerical simulations demonstrated the possibility of an intense vortex generation with a continuous positive dynamics as the shock crosses the interface. It was shown that while the vorticity is triggered by the shock refraction on the interface, it is the gas parameter distribution that distinctively determines the parameters of the vortex evolution. The proposed model also provides an insight into interesting aspects of the refraction effects for both, the shock wave and the flow behind it (double refraction). The results are applicable to the problems of energy deposition in a hypersonic flow, a flame-shock interaction, in combustion, in astrophysics, and in the fusion research.

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Section: C Power-law Density Distribution Casementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A mechanism of vortex generation in a supersonic flow behind a gas-plasma interface

Markhotok

2018

Fluid Dyn. Res.

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“…The results indicate broad possibilities to modify and control the SW front. [1][2][3] Any capability to modify the structure of a SW can reduce its strength and significantly decrease the shock induced drag, thus mitigating the effects of shocks in supersonic flight, heating problems during re-entry into the atmosphere, and reducing the effects of sonic booms. The changes in the SW front, such as its curvature, can possibly affect the structure of the detonation wave by affecting the ignition conditions through the dependence on the detonation speed.…”

Section: Introductionmentioning

confidence: 99%

Refractive phenomena in the shock wave dispersion with variable gradients

Markhotok

Popović

2010

Journal of Applied Physics

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In this article the refraction effects in the weak shock wave ͑SW͒ dispersion on an interface with a temperature variation between two mediums are described. In the case of a finite-gradient boundary, the effect of the SW dispersion is remarkably stronger than in the case of a step change in parameters. In the former case the vertical component of velocity for the transmitted SW ͑the refraction effect͒ must be taken into account. Results of comparative calculations based on the two-dimensional model corrected for the refraction effect show significant differences in the shapes of the dispersed SW fronts.

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“…Many studies, both computational and experimental have shown the efficacy of upstream energy deposition for shock wave modification (and resulting drag reduction) on blunt bodies (20)(21)(22)(23)(24) as well as potential drag reductions for forward-facing upstream injection (25)(26)(27)(28)(29)(30)(31) . Forward facing injection from blunt bodies in high-speed flows when coupled with upstream deposition of energy has recently been shown to result in large decreases in overall drag and heat transfer (32) .…”

Section: Upstream Energy Deposition and Upstream-directed Fluid Injecmentioning

confidence: 99%

Methods for the design of energy efficient high speed aerospace vehicles

et al. 2007

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This paper continues development of the fundamental analytical science, methodology and tools required for the analysis, design, and optimisation of high speed aerospace vehicles in terms of the efficient use of on-board energy. Specifically, it presents the complete second-law characterisation and related system-level energy management effectiveness for high-speed vehicles (coupling both aerodynamic and propulsive subsystems). Modelling of the fluid dynamics utilises high-level (multi-dimensional) flow-fields representative of generic configurations of interest. Capability has been recently developed which allows detailed second-law performance audits in terms of the 'common currency' of entropy generation for high-speed vehicles (involving complete synthesis of both internal and external flow-fields, i.e. both aerodynamic and propulsive sub-systems). This capability is now extended to encompass and utilise multi-dimensional flow-fields generated by computational fluid dynamics solvers, including Navier-Stokes solvers. Furthermore, the methodology is shown in this paper to provide insight and fundamental direction for management of onboard energy ('price paid') for maximum performance missions.

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An investigation of tailored upstream heating for sonic boom and drag reduction

Cited by 26 publications

References 1 publication

A mechanism of vortex generation in a supersonic flow behind a gas-plasma interface

A mechanism of vortex generation in a supersonic flow behind a gas-plasma interface

Refractive phenomena in the shock wave dispersion with variable gradients

Methods for the design of energy efficient high speed aerospace vehicles

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