Accession Number : AD0722693

Title :   Results of a Shock Tube Experiment in Compressible Turbulent Mixing.

Descriptive Note : Technical rept.,

Corporate Author : PURDUE UNIV LAFAYETTE IND PROJECT SQUID HEADQUARTERS

Personal Author(s) : Sanderson,Richard J. ; Steel,Peter C.

Report Date : MAR 1971

Pagination or Media Count : 40

Abstract : Two-dimensional supersonic turbulent mixing layers were produced with a small shock tunnel whose driven section is divided into two parallel chambers. When desired, combustion in the mixing layer was produced by use of oxygen in one stream and an argon-hydrogen mixture in the other. Variation in refractive index through the mixing layer was measured with a Mach-Zehnder interferometer and pressures were measured with piezo-electric transducers. From these measurements, freestream conditions could be computed. Approximate temperatures could be deduced directly from the interferograms throughout the mixing layer. A finite difference computer program which solves the turbulent conservation equations in terms of an empirical eddy viscosity model and a simple ignition delay-reaction time model for the chemistry was used to reconstruct the refractive index contours. Such an approach can describe the conditions in the mixing layer to an adequate degree of accuracy. It was found that for nonreacting mixing layers, the growth rates were comparable to those obtained from the literature for incompressible layers, and that the liberation of chemical energy increased mixing rates considerably, at least for the conditions of this experiment. (Author)

Descriptors :   (*SHOCK WAVES, TURBULENCE), SHOCK TUBES, BOUNDARY LAYER, TWO DIMENSIONAL FLOW, EXPERIMENTAL DATA, MATHEMATICAL MODELS, REFRACTIVE INDEX, COMBUSTION, COMPUTER PROGRAMMING, VISCOSITY, CHEMICAL PROPERTIES

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE