Direct numerical simulation of boundary layer receptivity to acoustic radiation in a hypersonic compression ramp flow

Hypersonic flight vehicle design has been a challenging, multidisciplinary field of study due to its complex nature. In the presence of increasing interest in air-breathing, hypersonic vehicles, we analyze the canonical flow system of a hypersonic 35^◦ compression ramp flow configuration that is known to involve unsteady flow phenomena such as—but not limited to—flow separation, leading edge bow shock, and reattachment shock. A high-order direct numerical simulation (DNS) in conjunction with experimental wind tunnel tests promise a more complete description of the flow features, with an aim to produce reliable reduced order models of them. Within the scope of this paper, we replicate experimental wind tunnel conditions including freestream disturbances based on experimental spectral pressure content including the boundary layer receptivity at the leading edge as well as laminar-turbulent transition which has been known to be critically important for an accurate simulation of compression ramp flows.