Boundary layer instabilities on bolt subscale geometry

John Thome, Anthony Knutson, Graham V. Candler

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

11 Scopus citations


We utilize the Navier-Stokes equations to study the amplification of perturbations in a three-dimensional boundary layer subject to continuous stochastic forcing. The freestream conditions correspond to recent experiments conducted in the Boeing/AFOSR Mach-6 Quiet Tunnel (BAM6QT) under quiet flow for a unit Reynolds number of 9.9 × 106 m−1. We first compute the steady flowfield and demonstrate how the Mach number and shape of the leading edge shock produce three-dimensional flow features using inviscid arguments. We then show agreement with experiments where infrared (IR) imaging reveal numerous streamwise heat streaks. Next, we perform an unsteady forced numerical simulation to investigate perturbation growth in the boundary layer. Sparsity-promoting dynamic mode decomposition (SPDMD) is used to extract the dominant modes from the forced numerical simulation. Using SPDMD and wall pressure data, we identify four distinct mechanisms of perturbation growth. The available experimental data agrees with the extracted modes in terms of frequency content demonstrating the predictive capabilities of our forced ‘quiet DNS.’.

Original languageEnglish (US)
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
StatePublished - Jan 1 2019
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: Jan 7 2019Jan 11 2019

Publication series

NameAIAA Scitech 2019 Forum


ConferenceAIAA Scitech Forum, 2019
Country/TerritoryUnited States
CitySan Diego


Dive into the research topics of 'Boundary layer instabilities on bolt subscale geometry'. Together they form a unique fingerprint.

Cite this