Direct numerical simulation of the aeroelastic response of a panel under high speed turbulent boundary layers

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 compression waves that oscillate with the panel motion. Turbulence statistics are shown to be modified by the presence of the compliant panel. Two way coupling is shown to be important.

Original languageEnglish (US)
Title of host publication43rd Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624102141
DOIs
StatePublished - 2013
Event43rd AIAA Fluid Dynamics Conference - San Diego, CA, United States
Duration: Jun 24 2013Jun 27 2013

Publication series

Name43rd Fluid Dynamics Conference

Other

Other43rd AIAA Fluid Dynamics Conference
CountryUnited States
CitySan Diego, CA
Period6/24/136/27/13

ASJC Scopus subject areas

  • Mechanical Engineering
  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology
  • Aerospace Engineering

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