“…A special wave complex featuring a recirculation zone is revealed due to the flow-wall interaction and ODW decoupling. The enhanced surface instability from the interaction is also shown to induce destabilization of the ODW structure (Wang et al 2020). However, the third aspect, namely the wave system of the reactive front in the initiation region, has not yet been investigated in detail.…”
“…A special wave complex featuring a recirculation zone is revealed due to the flow-wall interaction and ODW decoupling. The enhanced surface instability from the interaction is also shown to induce destabilization of the ODW structure (Wang et al 2020). However, the third aspect, namely the wave system of the reactive front in the initiation region, has not yet been investigated in detail.…”
“…According to our comparison, the deviation of our numerical simulation with experimental data and other computational studies is within an acceptable range (less than 11%). This deviation is acceptable in modeling of scientific and engineering problems 45 – 55 Figure 5 Validation of velocity profile velocity profile on the main nose body. …”
The importance of the cooling system for the design of the forebody of high-speed vehicles is significant due to severe aerodynamic heating at hypersonic flight. In the present study, injection of multi and single-coolant jets on the thermal performance of forebody design of nose cone with the cut spike is thoroughly investigated at hypersonic flow. A three-dimensional model of the blunt cone is presented for computational investigations of proposed jet and spike configurations. Injection of two coolant gasses (Helium and carbon dioxide) into the cooling system of the nose cone with a blunt spike is investigated. Three locations for both opposing and lateral jets are compared to find the efficient jet location. Our results indicate that a single lateral jet injected from the tip of the spike is more efficient for heat reduction. A comparison of the multiple injection system also shows that the heat reduction of the helium gas is about 15% more than CO2 jets.
“…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.…”
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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