SUPERSONIC LAMINAR BOUNDARY LAYER ALONG A 2-DIMENSIONAL ADIABATIC CURVED RAMP

The integral moment method of Lees and Reeves for an interacting, laminar boundary layer is applied to the problem of supersonic flows along a curved adiabatic ramp. This approach requires no prior knowledge of the separation point and can be used to treat relatively weak interaction, including a fully attached flow. It starts with small perturbations of the self-induced interaction on a flat plate; consequently, it can be applied to flows with the hypersonic interaction parameter x, based on the distance of beginning station of interaction to the leading edge, of the order 1. The effect of the radius of curvature on the separation phenomena is investigated using this method. The effect of the finite ramp length on the interaction is examined by making use of the characteristics of the singularities associated with the set of moment equations. Satisfactory agreement with theory was obtained for corresponding experiments conducted in the Mach 6 wind tunnel at the Graduate Aeronautical Laboratory of the California Institute of Technology. © 1969 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.