Abstract
Abstract : Experimental results of turbulent boundary layer-shock interaction at Mach 6 using a 10 deg axisymmetric wedge around an axisymmetric centerbody are presented and an effort is made to obtain a simple numerical solution of this problem by the time dependent unsteady method. Static pressure, pitot pressure and total temperature profiles, wall static pressure, heat transfer measurements and optical data were obtained. Air and hydrogen are injected to study their effects on the interaction region. Wall heat transfer and pressure distributions for different injection rates of both air and hydrogen are presented. Detailed mappings of Mach number, pressure distributions and shock wave locations are derived for the air injection as well as the no injection case. Experimental results show a natural boundary layer thickness of about .85 inches, a separated flow region about two inches long and a pressure plateau characteristic of turbulent flow. (Author)
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