Enhanced Thermal Conductance in Non Metallic Heat Exchanger

The Oblique Detonation Wave Hypervelocity Scramjet (ODW Hy-Scram) Engine is applicable to hypersonic flight vehicles that require high Mach Scramjet operation. This project will implement a unique new analysis capability to analyze and assess a novel propulsion device that could greatly enhance applications in the hypersonic class of flight vehicles. The ODW Hy-Scram Engine is configured to use gas dynamic wave interactions to provide inlet stream primary compression (after vehicle forebody compression), bulk ignition, and rapid combustion. The major advanatages over previous Scramjet engines are: 1) use of the vehicle forebody for fuel injection and complete mixing (due to longer distances, lower temperatures and lower pressures than is typical in the inlet fuel injection systems of Scramjet Engines), 2) simpler and shorter inlet design due to lower Mach range through which the flow must be decelerated (typically incorporated into the vehicle forebody), and 3) shorter and simpler combustor design. The primary benefit of this approach is the reduction of the weight associated with the propulsion system for a given combustion efficiency. The secondary benefit is stabilized combustion due to the bulk ignition of the fuel and oxidizer in the stable over driving of the oblique detonation wave.