Aeroelastic response of a panel under high speed turbulent boundary layers using direct numerical simulation

Christopher Ostoich, Daniel J Bodony, Philippe H Geubelle

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

Abstract

The interaction between a thin panel and a Mach 2.25 turbulent boundary layer is investigated using a high-accuracy, high-fidelity approach for the simulation of coupled fluid-structure problems. The solid solution is found by integrating the conservation of momentum equation using a non-linear 3D finite element solver, and the direct numerical simulation of the turbulent boundary layer uses a finite-difference compressible Navier- Stokes solver. The evolution of the panel response progresses from the emergence of low amplitude traveling bending waves to a larger amplitude standing wave type motion. Panel defections exceed 25 wall units into the boundary layer and produce weak shock waves that oscillate with the panel motion. Turbulence statistics are shown to be modified by the presence of the compliant panel.

Original languageEnglish (US)
Title of host publication51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
StatePublished - Aug 19 2013
Event51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 - Grapevine, TX, United States
Duration: Jan 7 2013Jan 10 2013

Publication series

Name51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

Other

Other51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
Country/TerritoryUnited States
CityGrapevine, TX
Period1/7/131/10/13

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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