Application of a transitional boundary-layer theory in the low hypersonic mach number regime

Abstract

An investigation is made to assess the capability of a finite-difference boundary-layer procedure to predict the mean profile development across a transition from laminar to turbulent flow in the low hypersonic Mach number regime. The boundary-layer procedure uses an integral form of the turbulence kinetic energy equation to govern the development of the Reynolds apparent shear stress. The present investigation shows the ability of this procedure to predict Stanton number, velocity profiles, and density profiles through the transition region and, in addition, to predict the effect of wall cooling and Mach number upon transition Reynolds number. The investigation also examines the contribution of the pressure dilatation term to the energy balance and suggests that transition can be initiated from the direct absorption of acoustic energy even if only a small amount (1 per cent) of the incident acoustic energy is absorbed.