Accession Number : ADA293836
Title : Compressible Turbulence Measurement in Low-Angle Injection into a Supersonic Flow.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : McCann, Gregory J.
PDF Url : ADA293836
Report Date : MAR 1995
Pagination or Media Count : 119
Abstract : Mean flow and compressible turbulence measurements have been obtained at two stations downstream of low-angle supersonic injection into a Mach 3.0 flow (Re/m = 15 x 106). Data were collected using conventional Pitot and cone-static probes, single and multiple overheat cross-wire anemometry, and flow visualization techniques (shadowgraphs and schlierens). A direct measure of total Reynolds shear stress was accomplished using a turbulence transformation of the Reynolds-averaged Navier-Stokes equations. Results show compressibility effects, indicated by density fluctuations, to be large relative to the velocity fluctuations and on the same order in all three components. Compressibility appears to account for as much as 75% of the total Reynolds shear. The results of the present study suggest turbulent compressibility effects are very important for this class of flows. (MM)
Descriptors : *TURBULENT FLOW, *FLOW VISUALIZATION, *COMPRESSIBLE FLOW, *SUPERSONIC FLOW, *GAS LASERS, *SUPERSONIC COMBUSTION RAMJET ENGINES, VELOCITY, COMPUTERIZED SIMULATION, DENSITY, THESES, TURBULENCE, FLOW FIELDS, SHEAR STRESSES, AEROSPACEPLANES, MACH NUMBER, NAVIER STOKES EQUATIONS, FLOW SEPARATION, STATIC PRESSURE, PITOT TUBES, REYNOLDS NUMBER, SUPERSONIC WIND TUNNELS, BOUNDARY LAYER FLOW.
Subject Categories : Lasers and Masers
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE