Detonation onset following shock wave focusing

Смирнов, Н.Н.; Penyazkov, O. G.; Sevrouk, K. L.; Никитин, В. Ф.; Стамов, Л.И.; Tyurenkova, V.V.

doi:10.1016/j.actaastro.2016.09.014

Cited by 90 publications

(14 citation statements)

References 22 publications

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“…In terms of the numerical method, turbulence is a difficult problem in flows and the current simulation equations for turbulence include Reynolds Averaged Navier-Stokes (RANS), Large Eddy, Separated Eddy, and Direct Numerical Simulation (DNS), etc. Considering the limitations of robustness and computational efficiency, RANS is still the main turbulence simulation method adopted at present [15]. When there are discontinuities in flows, the artificial viscosity, which can affect the calculation accuracy, is usually added to the central scheme to suppress oscillations.…”

Section: Introductionmentioning

confidence: 99%

An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

Zhang

2021

Applied Sciences

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Currently, aerothermal research into scramjet-propelled vehicles characterized by a wedge-shaped section is relatively sparse. Based on the Mach number, grid strategy, and numerical method, an effective simulation scheme for predicting the aerodynamic heat of a scramjet-propelled vehicle during flight is proposed in this paper. At different Mach numbers, the appropriate grid strategy and numerical method were determined by validation tests. Two-dimensional external flow field models based on wedge sections were established and, unlike in blunt bodies, the tests showed that at the high supersonic stage, the ideal cell Reynolds number should be no larger than 16. At the hypersonic stage, the ideal cell Reynolds number and aspect ratio of wall cells near the shock should be no larger than 40, and the AUSM+ flux type performs better than Roe’s FDS flux type at the above stages. The aerothermal prediction indicates that during a flight time of about 34 s, the temperature change reaches about 1913.35 °C, and the maximum average temperature change rate reaches 115 °C/s.

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Section: Introductionmentioning

confidence: 99%

An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

Zhang

2021

Applied Sciences

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“…To analyze the reaction rate of a hydrogen-air mixture, the one-step chemical reaction model is used, which follows ideal gas law [17]. The governing equations of continuity, momentum, and energy are solved simultaneously by the finite-volume method through commercial computational fluid dynamics (CFD) software ANSYS FLUENT 14.0 code [27][28][29][30][31][32][33][34]. A modified SIMPLEC scheme (Semi-Implicit Method for Pressure-Linked Equations-Consistent) is used to solve the Navier-Stokes equations.…”

Section: Mathematical and Combustion Modelingmentioning

confidence: 99%

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Alam

Sharma

Pandey

2019

J Braz. Soc. Mech. Sci. Eng.

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Pulse detonation engine is a new technique of supersonic wave propagation and stands for high impulsive thrust. The objective of the present investigation is to analyze the detonation wave characteristic of a hydrogen-air mixture in the pulse detonation engine (PDE) having obstacles of blockage ratio 0.5. The three-dimensional reactive Navier-Stokes equations with realizable k − ɛ turbulence model are used to simulate the propagation of combustion flame. The reaction rate of excess hydrogen and excess air is modeled by reduced single-step chemical reaction model and simulated using ANSYS software FLUENT 14.0 code. The simulation results of the shock wave overpressure, deflagration-to-detonation transition run-up distance of different flames and flame velocities are reported at initial boundary condition of 0.1 MPa pressure and 293 K temperature. It has been observed that the obstacles create turbulence in the propagating flame and form strong Mach stems of high temperature, resulting in reduction in accelerated flame run-up length. However, the normalized detonation flame run-up distance increases as the mass of fuel increases in the mixture. Thus, the performance of PDE combustor was observed 4.46% at high overpressure generated by excess fuel (ϕ = 1.3).

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“…The mathematical model for simulations of multi-component gas dynamics with chemical reactions including transport phenomena effects and turbulence was described in details in [11]. It contains the species mass, momentum and energy variation equations, which account for turbulent fluxes based on two-equation turbulence model of Wilcox komega [12].…”

Section: Mathematical Modelmentioning

confidence: 99%

Three-dimensional simulation of combustion, detonation and deflagration to detonation transition processes

Nickolay

Valeriy

2018

MATEC Web Conf.

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The paper presents results of numerical and experimental investigation of mixture ignition and detonation onset in shock wave reflected from inside a wedge. Contrary to existing opinion of shock wave focusing being the mechanism for detonation onset in reflection from a wedge or cone, it was demonstrated that along with the main scenario there exists a transient one, under which focusing causes ignition and successive flame acceleration bringing to detonation onset far behind the reflected shock wave. Several different flow scenarios manifest in reflection of shock waves all being dependent on incident shock wave intensity: reflecting of shock wave with lagging behind combustion zone, formation of detonation wave in reflection and focusing, and intermediate transient regimes. Comparison of numerical and experimental results made it possible to validate the developed 3-D transient mathematical model of chemically reacting gas mixture flows incorporating hydrogen – air mixtures.

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Detonation onset following shock wave focusing

Cited by 90 publications

References 22 publications

An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Three-dimensional simulation of combustion, detonation and deflagration to detonation transition processes

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