SCRAMJET NOZZLE DESIGN AND ANALYSIS AS APPLIED TO A HIGHLY INTEGRATED HYPERSONIC RESEARCH AIRPLANE

摘要

The great potential expected from future air-breathing hypersonic aircraft systems is predicated on the assumption that the propulsion system can be effi¬ciently integrated with the airframe. A study of engine-nozzle airframe inte¬gration at hypersonic speeds has been conducted by using a high-speed research-aircraft concept as a focus. Recently developed techniques for analysis of scramjet-nozzle exhaust flows provide a realistic analysis of complex forces resulting from the engine-nozzle airframe coupling. Results from these studies show that by properly integrating the engine-nozzle propulsive system with the airframe, efficient, controlled and stable flight results over a wide speed range.