Turbulent Mixing and Combustion
Abstract
The behavior of recirculating flows typical of advanced air-breathing and rocket injectors, as well as high energy chemical lasers, have been experimentally investigated. The configuration used consisted of a circular duct having a sudden increase of its diameter. Step size and flow velocity were chosen to be of a magnitude representative of 'sudden-dump' combustion chambers. The recirculation, which occurred in the separation region behind the sudden expansion, was investigated using a laser-Doppler velocimeter. Detailed measurements of the mean, axial, and radial velocities were made, as well as some measurements of turbulence intensity and shear stress. A set of partial differential equations - including continuity, axial and transverse momentum, turbulence energy, and turbulence dissipation - were derived and simultaneously solved using both integral and finite differencing techniques. Predictions made using these equations were brought into good agreement with the data taken from the recirculating flows under investigation by computer optimization of appropriate 'constants' in the models.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1975
- Accession Number
- ADA019659
Entities
People
- G. R. Salter
- G. Rudinger
- L. F. Moon
Organizations
- Bell Aircraft Corporation