Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet Flow

Abstract

Fundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with a nozzle exhaust plume. Aftbody shock waves that interact with the exhaust plume contribute to the near-field pressure signature of a vehicle. The plume and shock interaction is studied using computational fluid dynamics and compared with experimental data from a coaxial convergent–divergent nozzle flow in an open jet facility. A simple diamond-shaped wedge is used to generate the shock in the outer flow to study its impact on the inner jet flow. Results show that the compression from the wedge deflects both the nozzle plume and the shocks on the opposite side of the plume. The sonic boom pressure signature of the nozzle exhaust plume is modified by the presence of the wedge. Both the experimental results and computational predictions show changes in plume deflection and location of the shock from the wedge.