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

Fabian Dettenrieder, Bryson Sullivan, Antonio Schoneich, Stuart Laurence, Daniel J. Bodony

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

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.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2021 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-16
Number of pages16
ISBN (Print)9781624106095
StatePublished - 2021
EventAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online
Duration: Jan 11 2021Jan 15 2021

Publication series

NameAIAA Scitech 2021 Forum

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
CityVirtual, Online
Period1/11/211/15/21

ASJC Scopus subject areas

  • Aerospace Engineering

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