Plasma mitigation of shock wave: experiments and theory

Kuo, Spencer

doi:10.1007/s00193-007-0112-z

Cited by 22 publications

(11 citation statements)

References 19 publications

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“…Numerous recent experimental and theoretical investigations have shown that localized energy deposition in an upstream supersonic flow can substantially reduce aerodynamic drag of both blunt and streamlined bodies 1-10 and can be used for MHD control of inlet shock systems. 8 A number of authors reported on the complex structure of flow variation in this interaction. [11][12][13][14] In a localized, wall-free plasma discharge, interaction of shock waves with a stationary hot spot, or a layer generated by the off-board energy deposition to heat the gas, has long been acknowledged as an efficient means of ad-hoc flow control.…”

Section: Introductionmentioning

confidence: 98%

Shock wave refraction enhancing conditions on an extended interface

Markhotok

Popović

2013

Physics of Plasmas

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We determined the law of shock wave refraction for a class of extended interfaces with continuously variable gradients. When the interface is extended or when the gas parameters vary fast enough, the interface cannot be considered as sharp or smooth and the existing calculation methods cannot be applied. The expressions we derived are general enough to cover all three types of the interface and are valid for any law of continuously varying parameters. We apply the equations to the case of exponentially increasing temperature on the boundary and compare the results for all three types of interfaces. We have demonstrated that the type of interface can increase or inhibit the shock wave refraction. Our findings can be helpful in understanding the results obtained in energy deposition experiments as well as for controlling the shock-plasma interaction in other settings.

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Section: Introductionmentioning

confidence: 98%

Shock wave refraction enhancing conditions on an extended interface

Markhotok

Popović

2013

Physics of Plasmas

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“…Other approaches to the wave drag reduction are to use the focused energy deposition. A wide variety of energy deposition techniques were investigated by laser pulse, plasma arcs, microwaves, electron beams, pulsed detonations or explosions, etc [16][17][18][19][20][21] . When the focused energy is deposited in the upstream region of a blunt body, the extremely hot gas is created instantaneously to push the surrounding gas outward 17 .…”

Section: American Institute Of Aeronautics and Astronauticsmentioning

confidence: 99%

Conceptual study on non-ablative TPS for hypersonic vehicles

Jiang

Liu²,

Han³

2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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In order to achieve efficient wave drag reduction under non-zero attack angles and avoid the severe aerodynamic heating, a new concept of the Non-ablative Thermal Protection System (NaTPS) for hypersonic vehicles was proposed based on the idea that the conical shock wave angle can be enlarged by lateral jets to push the conical shock away from the blunt body surface. In the NaTPS, a spike-blunt body structure and lateral jets are combined together to develop a new shock-reconstructing system in front of hypersonic vehicles. When the spike acts to recast the bow shock in front of a blunt body into a conical shock, the lateral jet works to protect the spike tip from overheating and push the conical shock away from the blunt body when a pitching angle exists during flight. The experimental flow visualization and the pressure measurements were conducted in a hypersonic wind tunnel for both the conceptual demonstration and CFD validation. Numerical simulations were also carried out to examine the complex flow around the NaTPS. Both experimental and numerical results show that the NaTPS works well for shock drag reduction and thermal protection. The shock/shock interaction on shoulders of the blunt body is avoided due to lateral jet injection and the peak pressure at the reattachment region is reduced by 65% under a 4• attack angle. The lateral jet could be powered either by high pressure gas stored in the tank or by the water evaporation process in which water absorbs the heat from the hot walls of the blunt noses. The jet pressure needed for producing lateral jet is much smaller than for the forward-facing jet from the stagnation point. The advantages of this concept are well demonstrated and its practical application appears promising. Nomenclature

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“…The thermal plasma/gas regions are always present, for example, in the energy deposition experiments and they are described, in the absence of diffusion, as nonuniform gas objects, with a temperature profile for the initial temperature distribution that can be approximated with a Gaussian function. 23 The effects of the shock-plasma interaction have been an area of interest mostly due to its applications in aerospace for aerodynamic flow control in supersonic flights and for atmospheric reentry; 14,[24][25][26][27][28][29][30][31][32][33][34][35] in MHD for shock wave structure control; in astrophysics for shock waves generated in stellar interior; 15,16 and in environmental science for sonic boom suppression. Another area of considerable interest is the shock wave assisted combustion, where a shock wave can be used to affect the ignition conditions in the gas.…”

Section: Introductionmentioning

confidence: 99%

The cumulative energy effect for improved ignition timing

Markhotok

2015

Physics of Plasmas

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A technique capable of improving timing in ignition applications is proposed. It is based on the use of shock waves propagating in a specific medium that allows achieving extremely high speeds and energies. The model uses the energy cumulation effect in the presence of the shock wave refraction on an interface with plasma. The problem was solved analytically and the effects were demonstrated for a cylindrically symmetrical geometry. Numerical results show very quick and uneven acceleration of different portions of the shock front. Its strong distortions lead to formation of a sharply focused jet near the axis of symmetry. The ability of the shock to achieve extremely high speeds and energies can be useful in design of efficient combustors for hypersonic systems, and possibly offers an alternative way of construction of a nuclear fusion reactor. Recommendations are given in terms of adjustment parameters and can be applied at any problem scale and for various combinations of the strengths of the effects involved in the problem. V C 2015 AIP Publishing LLC. [http://dx.

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Plasma mitigation of shock wave: experiments and theory

Cited by 22 publications

References 19 publications

Shock wave refraction enhancing conditions on an extended interface

Shock wave refraction enhancing conditions on an extended interface

Conceptual study on non-ablative TPS for hypersonic vehicles

The cumulative energy effect for improved ignition timing

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