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Title: A Boundary Element Method iterative procedure to compute the compressible response of an airfoil subjected to incoming turbulence
Authors: Leandro de Santana, Leandro
Schram, Christophe
Desmet, Wim
Issue Date: 6-Jun-2014
Publisher: American Institute of Aeronautics and Astronautics
Host Document: 20TH AIAA/CEAS AEROACOUSTICS CONFERENCE
Conference: AIAA/CEAS AEROACOUSTICS CONFERENCE edition:20 location:Atlanta - USA date:06-09 June 2014
Article number: 2014-2323
Abstract: This paper proposes an innovative numerical technique for computing the aeroacoustic
response function of an airfoil subjected to incoming turbulence, accounting for trailing-
edge back-scattering effects and valid in the high-frequency subsonic compressible regime.
The methodology is based on the linearized potential flow equations, rewritten as the
Helmholtz equation, and solved using a Boundary Element Method (BEM) solver. This
approach permits to account for some realistic airfoil geometry effect. It has been validated
against Amiet theory for non-compact incident wavenumbers, showing good agreement
for both direct propagation and back-scattering correction. Finally, this methodology is
applied to a NACA-0012 wake-airfoil interaction case with wake parameters obtained from
experimental data, showing trends in good agreement with literature.
Publication status: published
KU Leuven publication type: IC
Appears in Collections:Production Engineering, Machine Design and Automation (PMA) Section

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