Steadiness of wave complex induced by oblique detonation wave reflection before an expansion corner

Wang, Kuanliang; Yang, Pengfei; Teng, Honghui

doi:10.1016/j.ast.2021.106592

Cited by 15 publications

(5 citation statements)

References 43 publications

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“…The throat width, denoted as H, signifies the distance from the shoulder of the projectile to the tube wall. The right boundary is set as an outlet with a zero-gradient Neumann boundary condition, which is widely adopted in previous studies on detonation waves [21][22][23]. In this study, we employ a mixture of hydrogen and oxygen at a stoichiometric equivalence ratio, along with additional nitrogen gas, as the incoming premixed fuel gas.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of the Oblique Detonation Waves and Stability in a Super-Detonative Ram Accelerator

2023

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This study numerically investigates the effects of diluent gas proportion, the overdrive factor, and throat width on the wave structure and thrust performance of a ram accelerator operating in super-detonative mode. For premixed gas of a high energy density, a typical unstart oblique detonation wave system is observed due to the ignition on the front wedge of the projectile, and the detonation waves move downstream to the shoulder as the energy density decreases. In the start range of the overdrive factor, the wave position also shows a tendency to move downstream as the projectile velocity increases, accompanied by oscillations of the wave surface and thrust. As the throat width increases, the wave standing position changes non-monotonously, with an interval of upstream movement and Mach reflection. The typical wave structure of a ram accelerator in super-detonative mode is identified, as well as the unstart stable wave features and the unstable process for choking, which can provide theoretical guidance for avoiding unstart issues in ram accelerators and optimizing their performance.

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Section: Introductionmentioning

confidence: 99%

Numerical Investigation of the Oblique Detonation Waves and Stability in a Super-Detonative Ram Accelerator

2023

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“…In particular, the additional factors involved in internal flows, such as the reflection of OSWs/ODWs (Wang et al. 2020 a , b ; Wang, Yang & Teng 2021), shock/detonation–shock/detonation interactions (Xiang et al. 2021 a , b ), shock/detonation–boundary layer interactions (Cai et al.…”

Section: Introductionmentioning

confidence: 99%

“…Wave reflection is a major feature in the inviscid ODW flow field in a space-confined ODE combustor (Lu, Fan & Wilson 2006; Wang et al. 2021; Xiang et al. 2021 b ), and its effects on ODW stabilization and the relevant mechanisms are important for the initial geometric design of the engine combustor.…”

Section: Introductionmentioning

confidence: 99%

“…However, the stabilization of an ODW induced by an isolated wedge or cone is only a typical external flow problem, whereas the stabilization of an ODW in an ODE combustor is an internal flow problem because of the geometric constraints of the combustor's internal walls. In particular, the additional factors involved in internal flows, such as the reflection of OSWs/ODWs (Wang et al 2020a,b;Wang, Yang & Teng 2021), shock/detonation-shock/detonation interactions (Xiang et al 2021a,b), shock/detonation-boundary layer interactions (Cai et al 2017(Cai et al , 2018a and shock/detonation-induced boundary layer separation (Ess, Sislian & Allen 2005;Miao et al 2020), increase the flow complexity in a space-confined combustor and cannot be overlooked in the stabilization of ODWs. These fundamental differences in detonation stabilization between spatially confined and unconfined flow regimes were also pointed out by Higgins (1997) through experiments, where hypervelocity blunt projectiles were fired into detonation chambers with significantly different chamber diameters and various detonation propagation phenomena were observed.…”

Section: Introductionmentioning

confidence: 99%

“…Wave reflection is a major feature in the inviscid ODW flow field in a space-confined ODE combustor (Lu, Fan & Wilson 2006;Wang et al 2021;Xiang et al 2021b), and its effects on ODW stabilization and the relevant mechanisms are important for the initial geometric design of the engine combustor. Figure 1 schematically shows two typical configurations of ODEs presented in previous literature (Schwartzentruber et al 2005;Alexander et al 2006;Wolański 2013) mixed-compression ODE.…”

Section: Introductionmentioning

confidence: 99%

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Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

2022

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The stabilization of oblique detonation waves (ODWs) in an engine combustor is important for the successful applications of oblique detonation engines, and comprehensively understanding the effects of the inviscid reflection of ODWs on their stabilization and the relevant mechanisms is imperative to overall combustor design. In this study, the flow fields of ODW reflections in a space-confined combustor are numerically studied by solving the two-dimensional time-dependent multispecies Euler equations in combination with a detailed hydrogen combustion mechanism. The inviscid Mach reflections of ODWs before an expansion corner are emphasized with different flight Mach numbers, Ma, and different dimensionless reflection locations, ζ ≥ 0 (ζ = 0: the ODW reflects precisely at the expansion corner; ζ > 0: the ODW reflects off the wall before the expansion corner). Two kinds of destabilization phenomena of the inviscid Mach reflection of an ODW induced by different mechanisms are found, namely wave-induced destabilization at large ζ > 0 for moderate (not very low) Ma and inherent destabilization at any ζ > 0 for low Ma. Wave-induced destabilization is attributed to the incompatibility between the pressure ratio across the Mach stem and its relative propagation speed, which is triggered by the action of the secondary reflected shock wave or the transmitted Mach stem on the subsonic zone behind the Mach stem. Inherent destabilization is demonstrated through an in-depth theoretical analysis and is attributed to geometric choking of the flow behind the Mach stem.

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Energy efficiency of detonation combustion in supersonic ramjet engines

Tunik

Mayorov

2022

Acta Astronautica

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Steadiness of wave complex induced by oblique detonation wave reflection before an expansion corner

Cited by 15 publications

References 43 publications

Numerical Investigation of the Oblique Detonation Waves and Stability in a Super-Detonative Ram Accelerator

Numerical Investigation of the Oblique Detonation Waves and Stability in a Super-Detonative Ram Accelerator

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

Energy efficiency of detonation combustion in supersonic ramjet engines

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