Accession Number : ADA322023
Title : (AASERT-93) Turbulent Reacting Flows at High Speed.
Descriptive Note : Final technical rept. 1 Sep 93-31 Aug 96,
Corporate Author : PRINCETON UNIV NJ
Personal Author(s) : Smits, Alexander J. ; Dryer, Frederick L. ; Fielding, J.
PDF Url : ADA322023
Report Date : 30 SEP 1996
Pagination or Media Count : 22
Abstract : A pilot-scale supersonic combustion tunnel was designed and constructed to operate with initial stagnation temperatures up to 900 K and static pressure and stagnation temperature ranges of 0.01-0.1 atm. and 290-900 K, respectively, in the test chamber without vitiation of the nitrogen/oxygen gas supply. Through the addition of hydrogen in the upstream settling chamber, the effective operating stagnation temperature in the test section was extended to 1100 K. The tunnel facility was instrumented with a Schlieren/shadowgraph system and charge-coupled device (CCD) intensified imaging of chemiluminescence from excited state hydroxyl radicals to study the initiation and combustion properties of nitrogen-diluted hydrogen/oxygen mixtures under Mach 3.0 flow conditions over both flat plate and wedge-shaped center bodies. Reaction initiation by recovery effects on noncatalytic and catalytic surfaces, as well as through seeding of the flow with radicals, was investigated.
Descriptors : *TURBULENT FLOW, *SUPERSONIC FLOW, *SUPERSONIC COMBUSTION RAMJET ENGINES, COMPUTATIONAL FLUID DYNAMICS, HYDROGEN, OXYGEN, FUEL AIR RATIO, IGNITION, LAMINAR FLOW, STATIC PRESSURE, STAGNATION TEMPERATURE, HYDROXYL RADICALS, SCHLIEREN PHOTOGRAPHY, SPARK SHADOWGRAPH PHOTOGRAPHY, LAMINAR BOUNDARY LAYER, JET MIXING FLOW, CHEMILUMINESCENCE.
Subject Categories : Fluid Mechanics
Jet and Gas Turbine Engines
Combustion and Ignition
Distribution Statement : APPROVED FOR PUBLIC RELEASE