Numerical modeling of standing oblique detonation waves

Glenn, Dennis E.; Pratt, David T.

doi:10.2514/6.1988-440

Cited by 8 publications

(2 citation statements)

References 3 publications

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“…Analyses have shown that the ODWE has comparable performance to the scramjet engine, with the main benefits of reduced engine size and increased thrust produced through pressure-gain combustion [5]. This has prompted analytical [6], experimental [7,8], and computational [9][10][11] work to understand the initiation and stabilization of ODWs on anchoring bodies. Previous studies have looked at blunt bodies and wedges, both as projectiles through reactive mixtures [12][13][14], and as stationary perturbations within premixed hypersonic flows [8,15,16].…”

Section: Introductionmentioning

confidence: 99%

“…This analysis enables the prediction of stability limits for a given mixture of gas at a given inflow static temperature and pressure, provided a value for Q can be determined by evaluation of some chemical kinetic model. Some of the first computational studies by Glenn and Pratt [9] and Li et al [10] began to validate the stability of the shaded region between the two limits. The latter study was the first to establish the typical structure of a wedge-stabilized ODW.…”

Section: Introductionmentioning

confidence: 99%

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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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