717 二次元超音速インテーク内部流動に関する実験的研究(OS7-6 航空宇宙推進(流体,燃焼))(OS7 北海道における航空宇宙工学研究の進展と未来)

概要

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In order to clarify characteristics 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 numerically by an computational fluid dynamics technique. A critical operation, where shocks induced by ramps attach to the leading edge of the cowl, is attained. A flow plug installed on the downward edge of the intake enables monotonous compression through a shock train caused by shock-boundary layer interactions.
一般社団法人日本機械学会の論文
2001-09-25