Book Description

The first of these 2 studies examined the detailed structure of the hypersonic boundary layer over a large cone/flare configuration. Emphasis was on development and use of instrumentation with which to obtain flow field measurements of the mean and fluctuating properties of the attached and separated shear layers. Development and use of holographic interferometry and electron beam techniques in the high Mach number and Reynolds number environment developed in the shock tunnel are described. In the second study, detailed measurements of heat transfer, pressure and skin friction were made on a unique 'blowing and roughness' model constructed to simulate the aerothermal phenomena associated with a rough ablating maneuverable reentry vehicle. In the 2nd study emphasis was placed on development and use of unique heat transfer and skin friction instrumentation to obtain measurements of the combined effects of blowing and roughness and to understand how such effects influence boundary layer separation in regions of shock wave/boundary layer interaction. Each focused around providing information with which to construct and evaluate the modeling required in time-averaged Navier-Stokes equations to predict the structure of compressible hypersonic boundary layers in regions of strong pressure gradient, shock wave/boundary layer interaction and flow separation over smooth, rough and ablating surfaces. (edc).