1990 年 10 巻 1Supplement 号 p. 53-56
The paper presents the flow behaviors within a supersonic air intake. It is redesigned in order to obtain a higher performance at Mach number 3. Flow visualization is made by using a vapor screen technique. A large scale of longitudinal vortices exists at the corner of the cowl surface and side wall due to the interaction of the oblique shock waves with the boundary layer.