On the Validation of a High-Order Large Eddy Simulation Solver for the Acoustic Prediction of Supersonic Jet Flow

A high-order large eddy simulation (LES) code based on the work of Stanford Aerospace Computing Laboratory called HiFiLES is further developed for supersonic jet flow simulation. The code uses a flux reconstruction method for spatial discretization and an explicit Runge-Kutta method for time advancement. LES with various subgrid scale models including static Smagorinsky, WALE, and similarity models are implemented. We implemented Persson’s shock detector with an exponential filter to capture discontinuities. A newly implemented Ffowcs-Williams and Hawkings acoustic solver is used for acoustic prediction. The acoustics solver relies on a new numerical probe technique to capture time histories of the flow-field variables. This numerical sampling technique is used for both acoustic prediction and flow-field validation. We validate our LES solver via examination of a supersonic off-design jet flow-field and acoustic data set from NASA Glenn Research Center. We present our modifications to the LES solver and validation results.