The proposed concept is the application of hot hydrogen from a compact, high-power (classiied) source to mix with, and heat ambient supersonic air in a scramjet duct to high temperatures. The study program will characterize such a system, investigating flow aerothermodynamics, induction of hot gas into a supersonic air flow, mixing times and dynamics, and determine the prospective isp for this type of scramjet. Phase ii effort will refine phase i codes (such as for hydrogen/supersonic air flow mixing), do detailed preliminary design of the hot gas scramjet -particularly of the inlet and mixing regions, perform bread-board testing of critical issues, and define the potential for meaningful phase iii experimental demonstrations.
Keywords: SCRAMJET DISSOCIATED HYD HOT HYDROBEN SUPERSONIC MIXI HIGH TEMPERATUR AEROTHERMODYNAM AIR FLOW POWER
