Abstract
The study of the interaction between detonation waves and flowfields could lead to a better understanding of combustion instability in rocket motors and to possible application to supersonic combustion. Apparatus was designed to measure the relative wave velocity and to photograph the wave profile as a fully developed detonation wave propagated against a flow of stoichiometric mixture of hydrogen-oxygen gases. The Mach number of the flowing unburned gas was varied from 0.14 to 4. The subsonic flow results were in good agreement with the Chapman-Jouguet theory; but the supersonic flow results indicated a strong detonation wave. The schlieren photographs of the wave indicated propagation into the boundary layer, and a convex curvature of the complete wave front was observed in the Mach 4 experiments. Velocity measurements indicated that the detonation wave was steady, but in some experiments disturbances were observed downstream of the detonation wave.
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