Numerical Investigation of Boundary-Layer Transition initiated by Random Disturbances for a Flat Plate at Mach 6

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

Abstract

Direct Numerical Simulations (DNS) were carried out in order to investigate the laminarturbulent transition process of a hypersonic boundary layer on a flat plate. The conditions of the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University were used for the simulations. Previous results from three-dimensional nonlinear wave packet simulations indicated that all the "classical" nonlinear mechanisms (fundamental resonance, oblique breakdown, subharmonic resonance) may be relevant for a hypersonic boundary-layer transition on a flat plate. For the present laminar-turbulent transition investigation, a random forcing approach is employed, which has been previously used as a model for "natural" transition without any bias towards a particular nonlinear mechanism.

Original languageEnglish (US)
Title of host publicationAIAA SciTech Forum 2022
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106316
DOIs
StatePublished - 2022
EventAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022 - San Diego, United States
Duration: Jan 3 2022Jan 7 2022

Publication series

NameAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Country/TerritoryUnited States
CitySan Diego
Period1/3/221/7/22

ASJC Scopus subject areas

  • Aerospace Engineering

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