A Boundary Element Method iterative procedure to compute the compressible response of an airfoil subjected to incoming turbulence | Zendy

Leandro D. de Santana | Zendy; Christophe Schram | Zendy; Wim Desmet | Zendy

Open Access

A Boundary Element Method iterative procedure to compute the compressible response of an airfoil subjected to incoming turbulence

Author(s) -

Leandro D. de Santana,

Christophe Schram,

Wim Desmet

Publication year - 2014

Publication title -

28th aiaa/ceas aeroacoustics 2022 conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.2014-2323

Subject(s) - airfoil , naca airfoil , physics , solver , boundary element method , compressible flow , wake , helmholtz equation , boundary value problem , turbulence , compressibility , mechanics , acoustics , mathematical analysis , finite element method , mathematics , mathematical optimization , reynolds number , thermodynamics

This paper proposes an innovative numerical technique for computing the aeroacousticresponse 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 theHelmholtz equation, and solved using a Boundary Element Method (BEM) solver. Thisapproach permits to account for some realistic airfoil geometry effect. It has been validatedagainst Amiet theory for non-compact incident wavenumbers, showing good agreementfor both direct propagation and back-scattering correction. Finally, this methodology isapplied to a NACA-0012 wake-airfoil interaction case with wake parameters obtained fromexperimental data, showing trends in good agreement with literature.status: publishe

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