Hydrogen-Fueled Scramjet Investigation
Abstract
This report documents an experimental and analytical study of the supersonic mixing and combustion processes associated with a free-shear layer. A specific objective comprised quantifying the effects on the mixing and combustion processes of pressure gradients associated with the production of shock waves in the flowfield. An experiment was conducted in a generic supersonic combustion configuration that incorporated the essential characteristics of scramjet combustors currently being considered for flight application. The objective of the analytical effort was to evaluate mixing and combustion models in state-of-the-art computational fluid dynamics (CFD) codes. The experiments provided accurate data used to formulate code input conditions and to evaluate codes that were formulated for application in current high-speed propulsion design activities. Species concentration, total and static temperature, and pitot pressure profiles were measured in a shear layer experiment in which gaseous hydrogen was injected tangentially into a Mach 3 (nominal) vitiated air stream. In this experiment, hydrogen was injected adjacent to the upperwall of the test section. A nonintrusive optical diagnostic technique was used in conjunction with intrusive probing to define the flowfield initial conditions and to characterize the detailed features of the flowfield subsequent to hydrogen injection and combustion.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1991
- Accession Number
- ADA237569
Entities
People
- L. Chiappetta
- T. J. Barber
- Travis J. Anderson
- W. J. Eckerle
- W. T. Peschke
Organizations
- United Technologies Corporation