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A critical concern for ASTOVL aircraft during landing manoeuvres is the deterioration in engine stability margin and performance due to the ingestion of hot gas from the engine exhaust into the engine inlets. This paper describes a methodology for the quantitative accounting of the effect of Hot Gas Ingestion (HGI) on engine stability and performance. To maximise performance and minimise design risk it is essential to have a technology data base to assess the likely HGI characteristics of candidate ASTOVL configurations and to identify measures to minimise HGI. This paper assesses the aircraft design features required to obtain low HGI characteristics for a wide range of ASTOVL configurations. Studies of steady-state CFD methods have commenced to determine their ability to model HGI flow paths of alternative aircraft configurations.

A propulsion system concept with particular application to supersonic short takeoff and vertical landing (STOVL) fighter/attack aircraft has been developed. The concept comprises a variable cycle engine, combining the advantages of a vectored thrust turbofan for takeoff, landing, and subsonic flight with those of a mixed augmented turbofan for high performance and supersonic flight. The system incorporates features and characteristics which have proved both practical and successful on the AV-8 (Harrier), and is potentially an attractive solution.