A MODEL FOR ADIABATIC SUPERSONIC TURBULENT BOUNDARY-LAYERS

An asymptotic analysis of the equations describing supersonic turbulen t flow over an adiabatic wall is carried out for high Reynolds numbers , Re, and mainstream Mach numbers, M(e) = O(1). A general expression f or the adiabatic-wall temperature is derived. The asymptotic theory co nstrains the types of turbulence models that are suitable to represent the effects of viscous dissipation. A simple algebraic turbulence mod el is proposed and comparisons with measured total enthalpy profile da ta show good agreement, capturing the overshoot observed in total enth alpy near the boundary-layer edge.