Experimental Observations on an Unsteady, Normal Shock/Boundary Layer Interaction,
Abstract
An experiment is described in which a normal shock interacts with the natural turbulent wall boundary layer in a parallel sided duct at Mach 1.3 and 1.5. The shock wave is vibrated in symmetric fashion by a rotating cam mounted in the tunnel diffuser. The design of this experiment, particularly the efforts to obtain a pure forcing signal, is discussed. Shock motion analysis at reduced frequencies of order 0.2 to 2 and amplitude parameters of 2% to 20% (based on equivalent chord) is presented. Unsteady surface pressure measurements under the interaction have been made and demonstrate that there is negligible phase change between the shock motion and the surface pressures. It appears reasonable to utilise quasi-steady assumptions in the calculation of the surface pressures at the low frequency conditions tested.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1987
- Accession Number
- ADP005510
Entities
People
- J. A. Edwards
- L. C. Squire
Organizations
- University of Cambridge