Affiliations: Beijing Institute of Aerodynamics, P.O. Box 7215,
Beijing 100074, China
Abstract: The complex separated flows induced by shock wave/boundary layer
interaction were studied at hypersonic speed of Mach number 5. The experimental
results on hypersonic flow over a set of rectangular cylinders are presented in
this paper. The rectangular cylinder mounted on a flat plate worked as a
typical model to simulate the obstacle on the vehicle surface. The effects of
flow interaction on the aerodynamic characteristics have to be predicted for
various geometrical parameters. So the static pressure distributions on the
model surface were measured, the complex shock wave system was shown by
schlieren photos, and the separated flow patterns around the obstacle were
visualized by oil flow technique. All of the results describe the interactive
flowfield features including peak pressure levels and their locations as well
as separated boundaries associated with influence regions.