Study on Flow Mechanism of Pseudo-Shock Waves in Scramjet Engine Isolators

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A normal shock wave in a constant area duct such as an isolator in a scram jet engine interacts with a wall boundary layer to form a pseudo-shock wave. Effects of the upstream boundary layer on a pseudo-shock wave are experimentally and theoretically clarified. Also, an optical system for measuring a complex shock containing supersonic flow quantitatively is presented. Further, compressible flow in curved ducts is experimentally studied.