Advanced Nozzle Technology.

This report contains a description of some of the exhaust concepts being developed as design options for use on the turbine engines which will power advanced fighter aircraft. Nozzle configurations which are not axisymmetric receive the major portion of the attention. Potential benefits of these types of nozzles are discussed and three general classes of nonaxisymmetric nozzles are described. Recent work in the areas of internal nozzle performance, cooling effectiveness, and structural integrity at minimum weight is discussed, and is used to establish the level of installation benefits which must be achieved to make these nozzles competitive with the more conventional axisymmetric configurations. The use of thrust vectoring to obtain improved normal load factor capability in an air superiority fighter was examined. Thrust accounting problems peculiar to certain nonaxisymmetric nozzles and certain thrust vectoring schemes are discussed. The report concludes with a short discussion of the further development required before these concepts can be considered as design options of acceptable risk. Author