No abstract

The selection and optimization of propulsion systems can be a costly and time-consuming process, especially when there are diverse performance requirements placed on the overall weapon system. Computerized procedures have been developed within the Grumman Propulsion Department to mechanize this capability and yet maintain the man-m-the-loop for full visibility during the evaluation of a candidate design concept. The system permits low cost, rapid, multidiscipline. interactive engine cycle selection and propulsion system integration to be effectively performed early in the preliminary design process of a high performance fighter aircraft. For example, the computer running time required to select a point design within a matrix of design variables and performance constraints has been reduced by 85 percent over previous techniques. This paper describes these propulsion evaluation procedures and cites a specific example of their application to the analysis of an advanced interceptor requirement.

Numerous studies aimed at evaluating the key advances in vehicle design have highlighted the importance of propulsion integration in the aircraft. This paper describes the design and integration of advanced nozzles in a future supersonic fighter.The requirements for such a nozzle include operation at high area ratio during supersonic cruise, vectoring for STOL field, performance and maneuvering, use of thrust reversers for combat and basing, good airframe integration, and high thrust performance with minimal thrust cooling losses. Such a nozzle configuration must also have favorable stealth characteristics in providing