Supersonic Separated and Reattaching Laminar Flows:I. General Theory and Application to Adiabatic Boundary Layer-Shock Wave Interactions

摘要

This report deals with laminar boundary layer-shock waveninteractions in which the pressure rise generated in an "external"nsupersonic, inviscid flow is communicated upstream through the boundarynlayer, and thereby induces flow separation. In order to describe thisnphenomenon approximately, including the subsequent reattachment of thenflow, we uti-lize an integral or moment method^in which the first momentnof momentum is employed, in addition to the usual momentum integraln(zero moment). By this means the velocity and enthalpy profiles arencharacterized by a single independent parameter not expiicitly related tonthe local static pressure gradient. This method itself is not new, butnit turns out that its successful application to separated and reattachingnflows hinges on the proper choice of the one-parameter family of velocitynprofiles utilized to represent the integral properties of the viscous flow.nWe show that the Stewartson reversed-flow profiles and their Cohen-nReshotko analogues for flows with heat transfer have the qualitativelyncorrect behavior; polynomials do not.