(AASERT-93) Turbulent Reacting Flows at High Speed.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 30, 1996
- Accession Number
- ADA322023
Entities
People
- Alexander Smits
- Frederick L. Dryer
- J. Fielding
Organizations
- Princeton University