SUPERSONIC MIXING AND COMBUSTION.
Abstract
One of the least understood but yet most important aspects of Scramjet Scientific Technology is the rate of turbulent mixing and combustion of supersonic fuel and air streams. An appreciable portion of this uncertainty stems from the lack of knowledge of the pertinent turbulent transport coefficients. This research is directed at improving the fundamental understanding of these phenomena by the application of non-interference diagnostics to well controlled experiments involving supersonic mixing with and without combustion. The report represents the first year's effort on this study. Design details of an experimental facility to investigate supersonic turbulent mixing are presented. Infrared spectroscopy, direct species sampling, and shadow photography are to be employed to determine, initially the rate of free mixing of both coaxial and paraxial streams at Mach 3. The working fluids are air and hydrogen or a hydrocarbon with hydrogen fluoride as a tracer molecule. The absorption of the fundamental rotation-vibration band of hydrogen fluoride is related to HF concentration by Abel integral inversion. It is shown that the Ladenburg-Reiche spectral line strength theory is applicable to non-homogeneous absorp media. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1968
- Accession Number
- AD0831896
Entities
People
- Clayton W. Lapointe
Organizations
- University of Michigan