In order to improve the operational efficiency of scramjet engines, it is necessary to develop new techniques to increase the mixing and flameholding properties at high Mach numbers of current scramjet designs. This paper investigates the high-temperature chemistry and plasmadynamic effects of a discharge arc in a supersonic shear layer. This is the first step in developing a clear understandin...

The results of experimental study of plasma-based mixing, ignition and flameholding in a supersonic model combustor are presented in the paper. The model combustor has a length of 600 mm and cross section of 72 mm width and 60 mm height. The fuel is directly injected into supersonic airflow (Mach number M=2, static pressure P(st)=160-250 Torr) through wall orifices. Two series of tests are focu...

Matsumura, Shin. Master of Science in Aeronautics and Astronautics, Purdue University, December, 2003. Streamwise Vortex Instability and Hypersonic BoundaryLayer Transition on the Hyper-2000. Major Professor: Steven P. Schneider. Despite the closely coupled multidisciplinary design of hypersonic airbreathing vehicles, the boundary layer transition mechanisms that are important on the forebody a...

Within this paper, control-relevant vehicle design concepts are examined using a widely used 3 DOF (plus flexibility) nonlinear model for the longitudinal dynamics of a generic carrot-shaped scramjet powered hypersonic vehicle. The impact of elevator size and placement on control-relevant static properties (e.g. level-flight trimmable region, trim controls, AOA, thrust margin) and dynamic prope...

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Three examples of response surface modeling with CFD are presented for combined cycle propulsion components. The examples include a mixed-compression-inlet during hypersonic flight, a hydrogen-fueled scramjet combustor during hypersonic flight, and a ducted-rocket nozzle during all-rocket flight. Three different experimental strategies were examined, including full factorial, fractionated centr...