Turbulent flow past two-dimensional bases in supersonic streams

Abstract

Experiments on the flow past two-dimensional, rearward-facing steps with turbulent approach boundary layers have been made at Mach numbers of 1.56, 2.41 and 3.10. Wide ranges of the ratio of boundary-layer thickness to step height were covered. The flow downstream of one step was briefly explored at a Mach number of 2.41. The base pressures are most conveniently expressed in terms of pressure-recovery coefficients for the flows downstream of the steps. Fairly good correlation of these coefficients is obtained by using the concept of local similarity upon which the measurement of skin friction by surface pitot tubes is based.