Experimental investigations on shock wave/boundary-layer interaction and its control at Mach=5

Abstract

Shock wave/boundary-layer interactions are ubiquitous in all transonic, supersonic and hypersonic flows and under most of the circumstances these interactions are detrimental to the performance of a flight vehicle. Despite great attention has been given to this flow phenomenon, three specific aspects are still being actively studied: prediction of heat transfer, interactions from complex configurations and flow control. This work deals with the interactions of a complex flat plate-fin-jet model and flow control on shock wave/boundary-layer interaction at the Mach number of 5. The following achievements have been obtained through this work: The flow field around a combined attitude control system, which consists of a aerodynamic control surface and a reaction control system, is fundamentally studied for the first time using a simplified flat plate-fin-jet model. The pressure distribution on the flat plate is measured using pressure sensitive paints, the structures of the shock waves and boundary layers are examined using schlieren and planar laser scattering. The interaction pattern between the shock wave and boundary layer, and the performance of the transverse jet as control device are compared among cases in which the jet is at different locations relative to the fin. The flow physics of the different interaction pattern is analysed and an optimized location of the jet is proposed based on the produced control force. A novel flow control technique using micro-scale herringbone riblets is investigated in terms of its performance of reducing flow separation induced by shock wave boundary layer interaction. Since the flat plate-fin-jet model is too complicated for a preliminary study of a new control device, a double ramp is used to test the control effectiveness of this control technique. The results show that herringbone riblets are capable of suppressing shock-induced flow separation and hence improving pressure recovery. It is also revealed that these micro-scale riblets induce large-scale streamwise vortical structures within the boundary layer, which have been only been previously identified in incompressible flows. It is believed that these vortices promote momentum transfer within the boundary layer hence providing the dominant mechanism for suppressing flow separation. Since the wind tunnel tests of both shock wave boundary layer interaction and its control involve using pressure sensitive paints, an exploratory investigation of applying pressure sensitive paints to a relatively simpler three-dimensional geometry of shock wave boundary layer interaction is conducted first to verify its capability. A canonical single/double wedge model on a flat plate is tested using pressure sensitive paints and temperature sensitive paints. The evolvement of the surface topological structure is revealed with the surface measurement result.

Date of Award	31 Dec 2018
Original language	English
Awarding Institution	The University of Manchester
Supervisor	Sergey Utyuzhnikov (Supervisor) & Shan Zhong (Supervisor)