
Accession Number : ADA118863
Title : An Experimental Investigation of the Unsteady Behavior of Blunt FinInduced Shock Wave Turbulent Boundary Layer Interactions.
Descriptive Note : Final technical rept. 21 Nov 8031 Dec 81,
Corporate Author : PRINCETON UNIV NJ DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
Personal Author(s) : Dolling,David S ; Bogdonoff,Seymour M
PDF Url : ADA118863
Report Date : May 1982
Pagination or Media Count : 46
Abstract : An experimental study has been made of blunt fininduced shock wave turbulent boundary layer interactions. This type of interaction is known to be highly unsteady. The objective of this experiment was to determine the characteristics of the fluctuating surface pressure distribution and the parameters controlling it. Tests have been made using fins of different diameter, D, with incoming turbulent boundary layers varying in thickness, Delta, in the ratio of about 5:1. Measurements have been made on the fin centerline and up to four diameters outboard of it. All tests were made at a Mach number of 2.95 and a unit Reynolds number of 6.3 billion/m, and under approximately adiabatic wall conditions. The measurements show that very high intensity r.m.s. pressure levels occurup to almost two orders of magnitude above that of the incoming boundary layer. The highest intensities occur on centerline ahead of the fin. Here, the r.m.s. pressure distribution is characterized by three distinct peaks which decrease at different rates with distance outboard. Even four diameters off centerline, the maximum r.m.s. value in the distribution is still an order of magnitude larger than that of the incoming boundary layer. Outboard of the centerline, the r.m.s. pressure level downstream of the freestream shock wave steadily decreases. Within a distance of six to eight diameters it is close to the undisturbed value. With different diameter fins and different boundary layers, the qualitative characteristics are the same. The quantitative results depend on the ratio D/Delta. (Author)
Descriptors : *Shock waves, *Turbulent boundary layer, Unsteady flow, Fins, Pressure distribution, Blunt bodies, Pressure measurement, Reynolds number, Wind tunnel tests, Wind tunnel models, Downstream flow
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE