Abstract
Heat release from detonation waves due to blunt bodies embedded into a constant area channel flow was studied numerically, solving laminar Navier-Stokes equations for chemically reacting nonequilibrium flows with a steady-state and time-accurate formulation. A maximum heat release is of interest in the context of propulsion applications, where the energy added to the flow can be utilized to increase thrust. Hence, channel blockage ratios (CBR), defined as the ratio of blunt-body diameter over channel height, in the range from 1/18 to 1/3 were examined for inflow conditions typical for a shock-induced combustion ramjet combustor of a hypersonic vehicle operating in a flight altitude of 38 km and a Mach number in excess of 10. The flow entering the domain at Mach number 5 is a stoichiometrically premixed hydrogen-air gas mixture that was modeled with 13 species and 33 chemical reaction equations.
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