Direct Numerical Simulation of Shock Impingement on a Compliant Panel at Mach 1.92

Direct numerical simulation (DNS) of shock impingement on a compliant panel at Mach 1.92 is implemented to analyze the effects of shock-wave/boundary-layer interactions (SBLI). The computational domain and flow conditions correspond to the experiment conducted by Brouwer et al. at the Air Force Research Laboratory, Research Cell 19 wind tunnel. Analysis is focused on fully characterizing the unsteady broadband fluid dynamic processes such as the unsteady temperature and pressure fields acting on the surface of the panel in the vicinity of the shock impingement location. Results are compared with corresponding measured data to establish the degree to which the simulation accurately predicts the observed flow characteristics. Additional quantitative information that cannot be measured is then extracted to further quantify key flow characteristics relevant to both modeling and the fundamental physics.