Optical Diagnostics in Supersonic Combusting Systems
Abstract
The development of supersonic combusting ramjet (SCRAMJET) engines requires testing using new, nonintrusive, instrumentation methods in high-speed, high-enthalpy flow facilities. This report describes a test series using a shock tunnel to produce Mach 3.0 flows with stagnation temperatures in excess of 3000 K and an optical diagnostic set specifically tailored for measurements in supersonic high temperature systems. The test facility includes a hydrogen injection capability which makes combustion tests possible for these flows. The report describes the shock tunnel and its capabilities, provides an overview of the optical diagnostics used in the test, and discusses the results of both combusting and noncombusting tests. The optical measurements include concentration and vibrational temperature for NO upstream of the combustion region (via spectrally resolved emission measurements), Planar Laser Induced Fluorescence (PLIF) imaging of both NO and OH (yielding either concentration or temperature information), and Schlieren photography. In addition, an OH absorption measurement strategy is discussed. This diagnostic set is particularly appropriate since it includes both line-of-sight and spatially resolved measurements and additionally, comparison of results form each of the techniques is possible.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1992
- Accession Number
- ADA253463
Entities
People
- H. H. Legner
- Kathleen Donohue
- Mark G. Allen
- R. R. Foutter
- S. J. Davis
- T. E. Parker
- W. T. Rawlins
- William G. Reinecke
Organizations
- Physical Sciences (United States)