Thermochemical non-equilibrium effects on hypersonic shock wave/turbulent boundary-layer interaction

Jiang, Hao; Liu, Jun; Luo, Shichao; Huang, Wei; Wang, Junyuan; Liu, Meikuan

doi:10.1016/j.actaastro.2021.12.010

Cited by 24 publications

(6 citation statements)

References 45 publications

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“…where e is the electron charge, n e is the electron density, and v e is the electron velocity. The electron velocity v e creating the polarization current J is derived by incorporating the ADE-FDTD algorithm into (10). It can be observed from ( 6) of the ADE-FDTD to compute the polarization current, and when particle collisions are taken into account, the polarization current emerges.…”

Section: Particle Model In Thermodynamic Non-equilibrium Statementioning

confidence: 99%

“…The results show that the thermochemical non-equilibrium effect of the Mach 12 inlet is significant under the condition of an adiabatic wall. Reference [10] developed a domestic parallel solver for hypersonic thermochemical non-equilibrium flow with the Reynolds-averaged Navier-Stokes (N-S) turbulence model. Using this solver, it is found that the combined effect of turbulence and thermochemical nonequilibrium has a significant impact on the flow field organization, wall data, and separation length of the shock/boundary layer interaction.…”

Section: Introductionmentioning

confidence: 99%

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Analysis of Low-Frequency Communication of Hypersonic Vehicles in Thermodynamic and Chemical Non-Equilibrium State

Wang,

Chen,

Wen

2023

Applied Sciences

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A plasma sheath will be developed surrounding a hypersonic vehicle in flight, which can reflect, absorb, and scatter electromagnetic (EM) waves of lower frequencies than its own, resulting in a communication blackout. This paper focuses on knowing how to limit the absorption and reflection of low-frequency EM waves by plasma sheath in a thermodynamic and chemical non-equilibrium state. According to the temperature increment model, the energy of high-power microwave (HPM) irradiation is translated into the temperature increment of heavy particles in plasma. As a result of this modification process, the transmittance of low-frequency EM waves going through the plasma sheath in a certain time frame rises, potentially easing the communication blackout problem.

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Section: Particle Model In Thermodynamic Non-equilibrium Statementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Analysis of Low-Frequency Communication of Hypersonic Vehicles in Thermodynamic and Chemical Non-Equilibrium State

Wang,

Chen,

Wen

2023

Applied Sciences

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“…[64] for a similar probe used in another hypersonic facility. While the possible sensitivity of the static pressure measurements to the thermochemical effects has not been rigorously assessed, it may be deduced from existing numerical flat plate studies with u∞ up to 6 km/s [65] that any sensitivity is likely negligible for the intent and purposes relevant to the current work. This is because any thermochemical effects in these very slender body flows are likely confined to the boundary layer with the inviscid flow remaining a calorically perfect gas since the shock wave from these bodies is very weak.…”

Section: Uncertaintiesmentioning

confidence: 99%

Characterization of reflected shock tunnel air conditions using a simple method

Olivier

Wen

et al. 2022

Physics of Fluids

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A new method to characterize air test conditions in hypersonic impulse facilities is introduced. It is a hybrid experimental-computational rebuilding method which uses the Fay-Riddell correlation with corrections based on thermochemical nonequilibrium computational fluid dynamic results. Its benefits include simplicity and time-resolution, and, using this method, a unique characterization can be made for each individual experimental run. Simplicity is achieved by avoiding the use of any optical techniques and overly expensive numerical computations while still maintaining accuracy. Without making any assumptions to relate the reservoir conditions to the nozzle exit conditions, the work done characterizing four test conditions in a reflected shock tunnel is presented. In this type of facility, shock compression is used to produce an appropriate reservoir which is then expanded through a nozzle to produce hypersonic flow. Particular focus is given to the nozzle exit total enthalpy where a comparison is made with the reservoir enthalpy obtained using the measured shock speed and pressure in the shock tube. Good agreement is observed in all cases providing validation of the new approach. Additionally, static pressure measurements showed clearly that conditions III and IV have a thermochemical state which likely froze shortly after the nozzle throat. Also, the nozzle flow is shown to be almost isentropic. Due to the simplicity of the current method, it can be easily implemented in existing facilities to provide an additional independent estimate alongside existing results.

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“…When a spacecraft reenters Earth's atmosphere or enters the interplanetary atmosphere, the flow surrounding the aircraft is characterized by high-temperature effects, such as the dissociation and even ionization of the fluid molecules flowing with hypersonic vehicles [1][2][3][4]. The high enthalpy tunnel can duplicate the high flow velocities and, subsequently, the high-temperature effects [5,6].…”

Section: Introductionmentioning

confidence: 99%

High Enthalpy Non-Equilibrium Expansion Effects in Turbulent Flow of the Conical Nozzle

et al. 2023

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High enthalpy stagnation gas can be converted into hypervelocity flow through the contraction—expansion nozzle. The enthalpy flow in the nozzle can be divided into three regions: an equilibrium region, a non-equilibrium region, and a frozen region. The stagnation gas with a total enthalpy of 13.4 MJ/kg is used to analyze the thermochemical non-equilibrium effects. At the selected conditions, the effects of a conical nozzle under different expansion angles of the expansion section, curvature radius of the throat, throat radius, and convergence angle of the convergent section are investigated. Based on the Spalart–Allmaras one-equation turbulence model with the Catris–Aupiox compressibility correction, a multi-block solver for axisymmetric compressible Navier–Stokes equations is applied to simulate the thermochemical non-equilibrium flow in several high enthalpy conical nozzles. The multi-species two-temperature equation is employed in the calculation. The results reveal three interesting characteristics: Firstly, the thermochemical non-equilibrium effects are sensitive to the maximum expansion angle and throat radius but not to the radius of throat curvature and contraction angle. Secondly, as the maximum expansion angle decreases and the throat radius increases, the flow approaches equilibrium state. When the maximum expansion angle decreases from 12° to 4°, the freezing temperature decreases from 2623 K to 2018 K. When the throat diameter increased from 10 mm to 30 mm, the freezing temperature decreased from 2442 K to 2140 K. Finally, the maximum expansion angle and throat radius not only affect the position of the freezing point but also the flow field parameters, such as temperature, Mach number, and species mass fraction.

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Thermochemical non-equilibrium effects on hypersonic shock wave/turbulent boundary-layer interaction

Cited by 24 publications

References 45 publications

Analysis of Low-Frequency Communication of Hypersonic Vehicles in Thermodynamic and Chemical Non-Equilibrium State

Analysis of Low-Frequency Communication of Hypersonic Vehicles in Thermodynamic and Chemical Non-Equilibrium State

Characterization of reflected shock tunnel air conditions using a simple method

High Enthalpy Non-Equilibrium Expansion Effects in Turbulent Flow of the Conical Nozzle

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