The refurbishment and commissioning of a hypersonic gun tunnel built in the 1960's, the collection of basic data, and the development of analytical methods at the University of Toronto Institute for Aerospace Studies (UTIAS) is described. Design improvements are underway to the gun piston employing modern numerical methods in fluid dynamics and stress analysis of high strength to weight materials. An advanced numerical simulation of the tunnel operation has been implemented involving gas flows in the driver, barrel, nozzle, and test section to that of the piston, and incorporating viscous and real-gas phenomena. The interactions of an oblique shock with a hypersonic boundary layer on a flat plate at concave and convex corners is being studied numerically to supplement similar experimental research conducted in the hypersonic impulse tunnel. An experimental study of hypersonic flow development in a circular pipe at a flow Mach number of about 8 has been undertaken to provide data to guide the development of fluid dynamics codes applicable to hypersonic internal flows. Experimental measurements were made on three different hypersonic compressive flow geometries (a Prandtl-Meyer inlet, a Busemann inlet, and a Oswatitsch inlet) so as to compare their efficacy as scramjet inlets. A computer code has been developed to compute unsteady gas flows through and around model hypersonic inlets that are being tested in the hypersonic impulse tunnel.


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