
Accession Number : AD0427156
Title : PRANDTL NUMBER DISTRIBUTION IN A TURBULENT BOUNDARY LAYER WITH HEAT TRANSFER AT SUPERSONIC SPEEDS,
Corporate Author : TEXAS UNIV AUSTIN DEFENSE RESEARCH LAB
Personal Author(s) : Rochelle,William C.
Report Date : OCT 1963
Pagination or Media Count : 1
Abstract : An investigation is described which determined the Prandtl Number distribution across a turbulent, compressible boundary layer, both with and without heat transfer at the wall. The calculations were performed by integrating the continuity, momentum, and energy equations, and by using an iteration process to determine the velocity and temperature profiles. Several assumed temperaturevelocity polynomials were developed and were checked for accuracy by means of the iteration process. Experimentally determined values of temperature, pressure, shear stress, heat transfer, Prandtl Number and velocity parameters and the Mach Number distribution across the boundary layer for two axial stations on a flat plate were used as the input parameters for an electronic digital computer. The Prandtl Numbers for the adiabatic cases ranged from about 0.89 near the wall to about 10 near the free stream for a wide range of Mach and Reynolds Numbers. For the heat transfer cases, the Prandtl Numbers varied from about 0.75 near the wall to a value of about 1.0 near the free stream when using a fourthorder temperaturevelocity equation. (Author)
Descriptors : (*TURBULENT BOUNDARY LAYER, SUPERSONIC CHARACTERISTICS), TEMPERATURE, VELOCITY, HEAT TRANSFER, SHEAR STRESSES, AERODYNAMIC HEATING, THERMAL CONDUCTIVITY, COMPRESSIBLE FLOW, THEORY, MATHEMATICAL ANALYSIS, MOTION, EQUATIONS, PARTIAL DIFFERENTIAL EQUATIONS, FLUID DYNAMICS, FLAT PLATE MODELS, SURFACES, FRICTION
Distribution Statement : APPROVED FOR PUBLIC RELEASE