| Abstract: | The development of disturbances in a hypersonic boundary layer on a cooled surface is investigated in the case in which the
characteristic velocity of disturbance propagation is small but greater than the flow velocity in the wall region of the three-layer
disturbed zone with interaction. The nonlinear boundary value problem formulated involves a single similarity parameter that
characterizes the contribution made by the main, on average either subsonic or supersonic, region of the boundary layer to
the generation of the pressure disturbance. In the linear approximation, an analytical solution and an algebraic dispersion
equation are derived. It is shown that only waves exponential in time and in the streamwise coordinate can propagate downstream
when themain region of the undisturbed boundary layer is subsonic on average. |
