Flow Structure and Aerodynamic Characteristics in a Supersonic Intake for Ramjet Propulsion

In order to clarify chalracteristics of supersonic intakes for ramjet engines flow structure around and through a small external-compression rectangular intake model with double ramps designed for Mach number 1.9 is investigated experimentally using a vacuum-type wind tunnel and a set of measurement methods composed of colored schlieren photography, laser Doppler velocimetry, and mercury manometry, as well as investigated numericalry by a computational fluid dynamics technique. A critical operation, where shocks induced by ramps attach to the leading edge of the coWL is attained. A fiow plug instaned on the downward edge of the intake enables monotonous compression through a shock train caused by shock-boundary layer interactions.小特集 : 「室蘭工大における航空宇宙工学研究の新展開