A Planar Reacting Shear Layer System for the Study of Fluid Dynamics- Combustion Interaction
Abstract
A versatile planar reacting shear layer (PRSL) facility is constructed at NASA Lewis Research Center. This paper describes the research objectives, as well as design, instrumentations and the operational procedures developed for the system. The fundamental governing equations and the type of quantitative information that are needed from experiments are described. Studies and reviews of current research in turbulent reacting flows have concluded a clear need for additional work in plane free shear layer systems. The importance of a planar reacting shear layer (PRSL) facility can be described in terms of space and aeronautics applications. For space applications, there is a need for development of methods to predict low thrust propulsion systems in terms of specific impulse and wall heat transfer as two examples. The design methodology of large rocket motors poorly predicts low thrust systems. For instance the hydrogen oxygen mixing layer of thruster can be simulated with a PRSL system. For aeronautics applications (i.e., high-speed propulsion), a PRSL system would make it possible to examine the effect of acoustic waves and the effect of combustion on mixing (e.g., gas temperature rise) and engine nozzles performance.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1990
- Accession Number
- ADA239249
Entities
People
- B. Ghorashi
- C. C. Wey
- C. J. Marek
- C. T. Chang
- C. Wey
- E. J. Mularz
Organizations
- National Aeronautics and Space Administration