-The scramjet performance of air-breathing hypersonic vehicle is highly correlated with flight height, Mach and angle of attack (AOA). The violent disturbance of the AOA can cause the engine power off. Consequently, the maneuverability of hypersonic vehicle is strictly limited in the cruising period. A composite control system for an air-breathing hypersonic vehicle is presented. The hypersonic...

This study investigates the effects of boundary layer combustion on skin friction reduction in a model scramjet combustor. The 4-equation RANS (Transition SST model) is employed as turbulence and one experimental case which involves supersonic turbulent used for validating numerical simulation method. Then wall jet device can be to inject hydrogen into designed added lower combustor engine. res...

Various optical methods are applied to study flame characteristics of a circular-cross-section combustor for Mach 10 scramjet. Experiments performed on direct-connected test facility fueled by hydrogen and driven using hydrogen/oxygen detonation. The is advantageous in solving thermal inhomogeneity, corner boundary layer aircraft integration problems. However, it difficult use traditional measu...

The cooling channel of a scramjet is the fundamental structure active thermal protection for an engine. Till now, studies have focused mainly on steady-state flow and heat transfer process in channel. However, vibration intensity engine increases sharply as flight speed increases, because which, exchange mechanisms based under stable conditions cannot be applied vibration. In this study, experi...

The weight of the oxidizer dominates the take-off weight of rocket based propulsion systems. Therefore, airbreathing engines that consume the oxygen from the atmosphere offer a promising alternative. At flight conditions with Mach numbers above 6 SCramjet propulsion systems represent a better suited concept than ramjet systems, as the high static temperature resulting from the deceleration to s...