Shock-Induced High-Speed Reactions in High Enthalpy Hypersonic Flow

Sosa, Jonathan; Rosato, Daniel A.; Ahmed, Kareem A.

doi:10.2514/6.2020-0924

Cited by 3 publications

(1 citation statement)

References 22 publications

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“…5.4. 2 models the upper half of the test section in the Mach 5 hypersonic combustor facility in the Center for Advanced Turbomachinery and Energy Research (CATER) at University of Central Florida (UCF), where the double-angle wedge was initially proposed for experimental testing of ODW stability in hypersonic hydrogen-air mixtures [38]. The inflow static temperature and Mach number are varied in both domains throughout the study, and the inflow static pressure is kept at 1 atm for all cases.…”

Section: Numerical Modelmentioning

confidence: 99%

Ignition criteria and the effect of boundary layers on wedge-stabilized oblique detonation waves

Bachman¹,

Goodwin²

2020

Preprint

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Simulations of a supersonic, premixed, reacting flow over a wedge were performed to investigate the effect of a boundary layer on the wedge surface on ignition and stability of oblique detonation waves (ODWs). Two computational domains were used: one containing a wedge of a single angle with a straight after-body, and the other containing a double-angle wedge geometry. Both domains were channels with a supersonic inflow of stoichiometric hydrogen-air and a nonreflecting outflow, and the wedge was modeled using an immersed boundary method. The compressible reactive Navier-Stokes equations were solved using a high-order numerical algorithm on an adapting grid. Inviscid and viscous wedge surfaces were modeled using slip and no-slip adiabatic boundary conditions, respectively. Inviscid wedge surface cases are presented for a range of inflow conditions and compared to previous work outlining several different ODW structures. An ignition criterion is established as an accurate method of predicting the formation of an ODW for a given inflow temperature, Mach number, wedge angle, and length of the inviscid wedge surface. A viscous wedge surface is then considered for a Mach 5 inflow at temperatures of 600 K, 700 K, and 800 K.The 600 K flow ignites in the boundary layer, but does not detonate, while the 700 K and 800 K flows ignite and form ODWs. It was determined that ODW formation depends on

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Section: Numerical Modelmentioning

confidence: 99%

Ignition criteria and the effect of boundary layers on wedge-stabilized oblique detonation waves

Bachman¹,

Goodwin²

2020

Preprint

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Numerical investigation of jet-wedge combinatorial initiation for oblique detonation wave in supersonic premixed mixture

Yao

Lin

2023

Physics of Fluids

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The jet-wedge combinatorial initiation (JWCI) is a novel functional form for initiating an oblique detonation wave (ODW) with reduced total drag within the oblique detonation combustor under the conditions of a low Mach number and low static pressure inflow. It can suppress the instability of the detached ODW. The evolution of the combustion wave during combinatorial initiation is dominated by the intersection between the bow shock wave (BSW) and the oblique shock wave (OSW), and consists of four stages: the shock-induced combustion stage, the shock-deflagration coupling stage, the hybrid combustion stage, and the oblique detonation stage. Three combustion regimes can be formed by using the JWCI: the shock-induced combustion regime, the hybrid combustion regime, and the oblique detonation combustion regime. These regimes have distinct characteristics of combustion and of flow structure that can be controlled by changing two non-dimensional variables: the ratio of momentum flux ( J) and the penetration ratio (PR). This is significant as it can facilitate the application of different combustion regimes under a variety of realistic flight conditions. In this study, the criterion for the transformation of the combustion regime is quantitatively investigated, and show that the structure of the combustion wave does not transform until both non-dimensional variables have reached their respective thresholds. J is crucial for determining the combustion regime and facilitating its transformation but the PR accounts only for the height of the combustion wave structure. The work is beneficial for research on the initiation of the ODW in applications of oblique detonation engines.

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