Mach 2 and Mach 3 mixing and combustion in scramjets

摘要: Experimental and theoretical studies are being conducted to explore techniques enhance mixing in scramjet combustors using parallel fuel injection from the base of swept unswept wall-mounted ramps. Parallel may be useful high speed scramjets due thrust contributed by momentum expanding that has been heated vehicle cooling cycle. The experiments reported herein were Mach 2 3 combustor inlet conditions. Supporting computational cold flow indicated observed enhanced for ramp configuration is primarily substantially higher degree vorticity entrainment generated trailing edges.