Undulated Splitter Plate Trailing Edge Effects on a Supersonic Nozzle

Spanwise perturbations on a splitter plate trailing edge are assesed as a means to mitigate a high frequency signal at 34kHz in a complex nozzle. The flowfield is comprised of two streams, mach 1.6 and mach 1 which merge behind a splitter plate, enter into a rectangular single expansion ramp nozzle (SERN) and exit over an aft-deck. The wavenumber implemented was guided by simulations as it showed a diminishment of the dominant tone by inducing streamwise vortices. Particle Image Velocimetry and pressure measurements are used to realize differences in the controlled flow from that of the nominal for various aft-deck lengths. The nominal and no deck configurations show an upwards vectoring of the mean jet plume whereas the half deck shows no change from the uncontrolled flow. The 34kHz tone ceased in the wavy splitter plate cases however other peaks were amplified. Spectral Analysis Modal Methods (SAMMs) will be leveraged to gain insight into the flow physics responsible for these amplifications.