Abstract
Experimental measurements are presented of the flow in a model supersonic-combustion ramjet. A rectangular duct with a central streamwise-injected planar hydrogen jet has been tested at various enthalpies in a free-piston-driven shock tunnel. Several optical diagnostic techniques were employed to characterize the flow for a moderate enthalpy condition where pressure measurements indicated that significant combustion was occurring. Shadowgraph and emission images provided qualitative information on the density variations and temperature distributions, respectively. The planar laser-induced fluorescence technique has been used to examine the regions of ignition. Combustion was found to be occurring only in a thin mixing layer present between the air and hydrogen streams. The positions of shock waves within the duct compared well with pressure measurements performed along the floor of the duct.
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