Investigation of Flat-Plate Hypersonic, Turbulent Boundary Layers With Heat Transfer

Abstract

Naturally turbulent boundary layers on a cooled flat plate have been investigated at several distances from the leading edge of the plate at a Mach number of 5.2 for three rates of steady-state heat transfer to the surface. Measurements of Pitot and static pressures and of total and wall temperatures made it possible to compute velocity profiles, static-temperature profiles, and boundary-layer parameters without resorting to assumptions. The data demonstrate that the Reynolds analogy between skin friction and heat transfer is valid for all conditions of the present experiments. With increasing rate of heat transfer to the surface, the skin-friction coefficient was found to decrease, a phenomenon opposite to that predicted by theories and empirical relations. On the basis of the present data and other published results of compressible and incompressible turbulent boundary-layer skin friction, a simple relation was devised which describes closely the variation of the skin-friction coefficient with Mach number, heat-transfer rate, and momentum-thickness Reynolds number.

Laminar and Turbulent Boundary Layers on Slightly-Blunted Cones at Hypersonic Speeds

“…The relations given in both references differ somewhat from equations (3) and (4). The present results have been compared with experimental skin friction coefficients of references (6), (9), (10), (11), (12), and (13) which cover the range of M l from 1.7 to 7.0 and (TT, -Tw)/TT, from 0.04 to 0.84. There is reasonable agreement between theory and experiment.…”

“…For Tw = constant and n = constant, the following result can be obtained from equations (12) and (13) …”

An experimental investigation of heat transfer from a highly cooled turbulent boundary layer.

“…The Winkler and Cha correlation equation for the skinfriction coefficient in a compressible, turbulent boundary layer is based on experimental data obtained in a hypersonic wind tunnel. 20 In terms of enthalpy, the Winkler and Cha equation may be written as (9) where c fi is that for incompressible flow and may be evaluated using Eq. (3).…”