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The Propulsion Aerodynamics Branch (and its predecessors) at the NASA Langley Research Center has been conducting propulsion aerodynamics research since 1941. During that time, branch research has had an impact on almost every aircraft flown. Before 1982, the primary contribution was in the form of experimental data obtained in the 16-Foot Transonic Tunnel and an associated static test facility. During the last decade, computational fluid dynamics research has played an increasing role in branch contributions. This paper provides an overview of the propulsion/airframe integration activities conducted in the branch during the last several years and some indication of the direction of future research.

Future fighter aircraft must possess improved performance over a broader range of flight conditions than previously thought possible. Much of this improved performance will be directly related to propulsion system advances. In particular, multiaxis thrust vectoring nozzles have the potential of providing substantial airplane performance gains or even providing new capabilities. Because of the large benefits of multiaxis thrust vectoring, the Propulsion Aerodynamics Branch of the NASA Langley Research Center has conducted an extensive experimental research program in this area. These programs include both static and wind-on performance evaluations of a multitude of multiaxis thrust vectoring nozzle concepts. Results from some of these experimental programs are presented. Performance comparisons of several of the more feasible concepts are shown.