Supersonic mixing and combustion in scramjetsExperimental and theoretical studies are being conducted to explore techniques to enhance mixing in scramjet combustors using parallel fuel injection from the base of swept and unswept wall-mounted ramps. The experiments reported herein were conducted using Mach 2 and 3 combustor inlet conditions. Supporting computational and cold flow studies indicated that the observed enhanced mixing for the swept ramp configuration is primarily due to the substantially higher degree of vorticity and entrainment generated by the swept trailing edges.
Document ID
19910071572
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Northam, G. B. (NASA Langley Research Center Hampton, VA, United States)
Capriotti, D. P. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Byington, C. S. (Pennsylvania State University University Park, United States)
Greenberg, I. (Rafael Armament Development Authority Haifa, Israel)