Integral moment method of L.Lees, B.L. Reeves for interacting, laminar boundary layer is applied to problem of supersonic flows; approach requires no prior knowledge of separation point and can be used to treat relatively weak interaction, including fully attached flow; it starts with small perturbations of self-induced interaction on flat plate; it can be applied to flows with hypersonic interaction parameter, based on distance of beginning station of interaction to leading edge, of order one; satisfactory agreement with theory was obtained for corresponding experiments conducted in Mach 6 wind tunnel at Graduate Aeronautical Laboratory of California Institute of Technology. (23296)
Supersonic laminar boundary layer along two-dimensional adiabatic curved ramp
AIAA J
AIAA Journal ; 7 , n 2
1969
7 pages
Article (Journal)
English
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