Magnetohydrodynamic Interaction in the Shock Layer of a Wedge in a Hypersonic Flow

Borghi, C.A.; Carraro, Mario; Cristofolini, Andrea; Veefkind, A.; Biagioni, L.; Fantoni, G.; Passaro, A.; Capitelli, M.; Colonna, G.

doi:10.1109/tps.2006.883377

Cited by 23 publications

(9 citation statements)

References 12 publications

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“…However, the number densities of electrons and positively charged ions are lower than 10 13 /cm 3 . The negatively charged ions number density has a value even sparser than that of its positively charged counterpart [30].…”

Section: Inelastic Collision Ionization Modelmentioning

confidence: 92%

“…This behavior reflects a reduction of ionization efficiency. The inelastic collision model has been exclusively applied to plasma-based flow control actuators for hypersonic flow control [2,3]. The key mechanism of DCD is based on the thermal effect that derived from Joule heating in the cathode layer immediately above the cathode in addition to the electrode heating.…”

Section: Computational Simulationsmentioning

confidence: 99%

“…The cathode layer thickness decreases as the ambient density is increased, and the width of the cathode layer also shrinks from 2.66 to 0.58 cm corresponding to the pressure rise from 3 to 10 Torr [22]. The inelastic collision model has been exclusively applied to plasma-based flow control actuators for hypersonic flow control [2,3]. The key mechanism of DCD is based on the thermal effect that derived from Joule heating in the cathode layer immediately above the cathode in addition to the electrode heating.…”

Section: Computational Simulationsmentioning

confidence: 99%

“…Although the electrically conducting medium is globally neutral, it infuses additional mechanisms in the form of remote acting force by electrostatic and Lorentz accelerations, as well as by Joule heating. Joule heating provides a flow control mechanism by modifying the boundary-layer displacement distance over the electrodes that leads to virtue leading edge [2,3] and virtual variable inlet cross-section area inlet [4] applications. In the region of charge separation, the periodic electrostatic force is the mechanism for flow control using plasma actuators [5].…”

Section: Introductionmentioning

confidence: 99%

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Modeling Plasma via Electron Impact Ionization

Shang

2018

Aerospace

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Variable and potential plasma applications in aerospace engineering are exemplified by ion thrusters, flow control by plasma actuator, enhanced ignition and combustion stability. The operational environments span a range from the rarefied to continuum gasdynamic regimes; however, the ionization process in practical applications is mostly by electron impact. The fundamental ionization mechanisms by electron impact consist of electron secondary mission and the cascading process. In an alternating electric field, unsteady and random micro discharges or streamers are always presented; therefore the discharge physics imposes a formidable challenge for incisive understanding. Meanwhile, the ionized species constitute hundreds of metastable chemical species; under this circumstance the physics-based modeling for analyzing the inhomogeneous medium becomes necessary. A summary of the physics-based modeling for electron impact ionization from the Boltzmann distribution equation to the inelastic particle kinetics formulation is delineated.

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Section: Inelastic Collision Ionization Modelmentioning

confidence: 92%

Section: Computational Simulationsmentioning

confidence: 99%

Section: Computational Simulationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Modeling Plasma via Electron Impact Ionization

Shang

2018

Aerospace

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“…(5). The self-consistent approach, without radiation transport, has been applied to nozzle expansion for different mixtures [51][52][53], also in presence of applied electric and magnetic fields [54,55], in the boundary layer of hypersonic vehicle [56,57], a 2D flow around a cylinder [58] and in gas discharges [59], neglecting the radiation. Recently, a full model also including radiation transfer is being developed and applied to 1D shock waves in hydrogen [17] and hydrogen-helium (Jupiter atmosphere) mixtures [18].…”

mentioning

confidence: 99%

Advanced Models in Shock Waves

Colonna¹,

Ammando²,

Dikalyuk³

et al. 2014

TOPPJ

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Abstract:The paper presents three collisional-radiative models developed to investigate non-equilibrium chemistry and radiation in hypersonic shock tubes operating with different planetary atmospheres. An hybrid collisional-radiative model, employing the state-to-state kinetics of electronically excited states of molecules and the multi-temperature approximation for the vibrational degree of freedom is presented first, and applied to the numerical rebuilding of experimental shock tube emission spectra. Next, an hybrid collisional-radiative model for ionized air is presented. This model consider the state-tostate approach for electronic states of atoms and the multi-temperature model for the vibrational populations of diatomic molecules in their ground electronic state. A radiative transport equation is also solved to determine radiative source terms in the kinetic scheme and the enthalpy production due to radiation. The third model considers the state-to-state collisionalradiative model of Jupiter's atmosphere, self-consistently coupled with the Boltzmann equation for free electrons and the radiative transfer equation for the radiation transport in one-dimensional slab geometry.

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Joule‐Heating Actuators

Shang¹

2016

Computational Electromagneticaerodynamics

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Magnetohydrodynamic Interaction in the Shock Layer of a Wedge in a Hypersonic Flow

Cited by 23 publications

References 12 publications

Modeling Plasma via Electron Impact Ionization

Modeling Plasma via Electron Impact Ionization

Advanced Models in Shock Waves

Joule‐Heating Actuators

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