Model reduction for nonlinear aeroelasticity using the Discrete Empirical Interpolation Method

W. Yao, S. Marques

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

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Abstract

A novel surrogate model is proposed in lieu of computational fluid dynamic (CFD) code for fast nonlinear aerodynamic modeling. First, a nonlinear function is identified on selected interpolation points defined by discrete empirical interpolation method (DEIM). The flow field is then reconstructed by a least square approximation of flow modes extracted by proper orthogonal decomposition (POD). The proposed model is applied in the prediction of limit cycle oscillation for a plunge/pitch airfoil and a delta wing with linear structural model, results are validate against a time accurate CFD-FEM code. The results show the model is able to replicate the aerodynamic forces and flow fields with sufficient accuracy while requiring a fraction of CFD cost.
Original languageEnglish
Title of host publicationProceedings for Royal Aeronautical Society 5th Aircraft Structural Design Conference
PublisherRoyal Aeronautical Society
Number of pages16
Publication statusPublished - 01 Nov 2016
EventRoyal Aeronautical Society 5th Aircraft Structural Design Conference - Manchester Conference Centre, Manchester, United Kingdom
Duration: 04 Oct 201606 Oct 2016
http://www.aerosociety.com/Events/Event-List/1980/5th-Aircraft-Structural-Design-Conference (Link to event details online)

Conference

ConferenceRoyal Aeronautical Society 5th Aircraft Structural Design Conference
CountryUnited Kingdom
CityManchester
Period04/10/201606/10/2016
Internet address

Keywords

  • nonlinear
  • aeroelasticity
  • ROM
  • CFD
  • LCO

ASJC Scopus subject areas

  • Aerospace Engineering

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  • Cite this

    Yao, W., & Marques, S. (2016). Model reduction for nonlinear aeroelasticity using the Discrete Empirical Interpolation Method. In Proceedings for Royal Aeronautical Society 5th Aircraft Structural Design Conference Royal Aeronautical Society.