Mach 6-8 Scramjet Combustion Experiments using Hydrocarbon Fuel
Abstract
This project proposes to test high speed combustion phenomena at scramjet conditions in a shock tunnel with a large scale axisymmetric isolator and combustor using hydrocarbon fuels. Tests will be conducted as a combustor in a freejet flow, allowing multiple combustor configurations and robust control of boundary layer ingestion. Combustion will be visualized using planar laser induced fluorescence (PLIF) at multiple streamwise stations, allowing investigation of fuel jet penetration and mixing, flame propagation and extinction.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 23, 2016
- Source ID
- FA23861514093
Entities
People
- Michael Kevin Smart
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Queensland