With scramjets displaying improving performance within the wider literature, attention is turning towards airframe-integrated systems for access-to-space. The Mach 12 Rectangular-to-Elliptical Shape-Transitioning (M12REST) engine has been designed to operate at upper flight speeds, leading towards operable hybrid launch vehicles. At these speeds, internal components must be tuned to experience minimal losses and heating loads. To this end, the present work, guided by prior simulations, both shortens the M12REST combustion chamber by 57.5%, and removes the legacy backwards facing step. The newly configured combustor was examined experimentally at on-design conditions within the T4 Stalker Tube at The University of Queensland. Heat transfer analysis indicated significant combustion of hydrogen fuel was achieved through the combustor, with substantial pressure rises measured on the thrust nozzle surface.
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