Abstract
A detailed steady-state five-hole cone probe pressure survey of vectored and nonvectored exhaust plumes was conducted in the AFWAL Trisonic Gasdynamics Facility. Data were collected at a freestream Mach number of 0.5 for a convergent nozzle with an aspect ratio of 11 that was integrated into the wing trailing edge of a halfspan wing/body configuration. Selected cross-sectional pressure and Mach number maps between 0 and 40 nozzle heights downstream are presented. Analysis indicates that the vectored nonaxisymmetric exhaust plume exhibits an accelerated rate of mixing and diffusion, primarily the result of a component of the jet in crossflow rather than the influence of the wing/body flowfield.
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