The Effect of Chemical Reactivity on the Formation of Gaseous Oblique Detonation Waves

Aerospace

HoiDick Ng¹  Chian Yan¹  XiaoCheng Mi²  HongHui Teng³ 

[1] Department of Mechanical, Industrial and Aerospace Engineering, Concordia University, Montreal, QC H3G 1M8, Canada;Department of Physics, Cavendish Laboratory, University of Cambridge, Cambridge CB3 0HE, UK;School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;

关键词: propulsion;    oblique detonation;    CFD;    supersonic combustion;    chemical kinetics;   

DOI  :  10.3390/aerospace6060062

来源: DOAJ

【 摘 要 】

High-fidelity numerical simulations using a Graphics Processing Unit (GPU)-based solver are performed to investigate oblique detonations induced by a two-dimensional, semi-infinite wedge using an idealized model with the reactive Euler equations coupled with one-step Arrhenius or two-step induction-reaction kinetics. The novelty of this work lies in the analysis of chemical reaction sensitivity (characterized by the activation energy E_a and heat release rate constant k_R) on the two types of oblique detonation formation, namely, the abrupt onset with a multi-wave point and a smooth transition with a curved shock. Scenarios with various inflow Mach number regimes M₀ and wedge angles θ are considered. The conditions for these two formation types are described quantitatively by the obtained boundary curves in M₀−E_a and M₀−k_R spaces. At a low M₀, the critical E_a,cr and k_R,cr for the transition are essentially independent of the wedge angle. At a high flow Mach number regime with M₀ above approximately 9.0, the boundary curves for the three wedge angles deviate substantially from each other. The overdrive effect induced by the wedge becomes the dominant factor on the transition type. In the limit of large E_a, the flow in the vicinity of the initiation region exhibits more complex features. The effects of the features on the unstable oblique detonation surface are discussed.

【 授权许可】

Unknown