High-Order Finite-Difference Large-Eddy Simulations of a Supersonic Nozzle

Large-eddy simulations of the flow emanating from supersonic nozzles were carried out for the 6th Propulsion Aerodynamics Workshop to be held at the AIAA SciTech Conference. The purpose of the work is to detail the ability of a high-order of accuracy finite-difference based numerical scheme to accurately compute this flow. Results for both a perfectly expanded and over-expanded flow case are presented. Several complicating factors are discussed: 1) the limitations on the computational grid imposed by the numerical method, 2) the effect of additional dissipation necessary to resolve shock waves and 3) the effect of the nozzle boundary layer on the flow. Results indicate that the simulations replicate the basic flow physics, but there is room for improvement in accuracy. Areas for future study are outlined.