Measurment of hypersonic flow fields around a Sidewall compression scramjet inlet using shock tunnel experiments

摘要

Towards elucidating the aerodynamic forces produced by the spillage flow field around the lo3er inlet area of a sidewall compression type scramjet inlet, model experiments were carried out in the middle-scale shock tunnel of the national Aerospace laboratory, Japan. Pitot pressure measurements at hypersonic flow speeds were obtained of (i) the boundary layer which develops on the under surface of the forebody directly upstream of the inlet entrance and (ii) the spillage flow field directly under the throat area.