Numerical simulations of oblique detonations in supersonic combustion chambers

The concept of oblique detonation waves has been suggested as an efficient mechanism for ignition of the combustible mixture in a scramjet. To verify this concept, both experimental and numerical capabilities must be developed. We have developed an inviscid, two-dimensional numerical scheme coupled to the detailed reaction kinetics of combustion. The scheme is second-order-accurate total variation diminishing, time accurate, and couples the chemistry via an operator-splitting method. The code is fully vectorized for maximal efficiency and has been applied to the study of oblique detonations at various conditions of pressure and Mach number. The method is discussed in the paper, as well as the numerical results pertinent to the proof of concept of the oblique detonation wave engine.