Nonlinear Aerodynamic and Aeroelastic Model Reduction using a Discrete Empirical Interpolation Method

W. Yao, S. Marques

Research output: Contribution to journalArticle

6 Citations (Scopus)
477 Downloads (Pure)

Abstract

A novel surrogate model is proposed in lieu of computational-fluid-dynamics solvers, for fast nonlinear aerodynamic and aeroelastic modeling. A nonlinear function is identified on selected interpolation points by a discrete empirical interpolation method. The flowfield is then reconstructed using a least-square approximation of the flow modes extracted by proper orthogonal decomposition. The aeroelastic reduced-order model is completed by introducing a nonlinear mapping function between displacements and the discrete empirical interpolation method points. The proposed model is investigated to predict the aerodynamic forces due to forced motions using a NACA 0012 airfoil undergoing a prescribed pitching oscillation. To investigate aeroelastic problems at transonic conditions, a pitch/plunge airfoil and a cropped delta wing aeroelastic models are built using linear structural models. The presence of shock waves triggers the appearance of limit-cycle oscillations, which the model is able to predict. For all cases tested, the new reduced-order model shows the ability to replicate the nonlinear aerodynamic forces and structural displacements and reconstruct the complete flowfield with sufficient accuracy at a fraction of the cost of full-order computational-fluid-dynamics model.
Original languageEnglish
Pages (from-to)624-637
Number of pages14
JournalAIAA Journal
Volume55
Issue number2
Early online date11 Jan 2017
DOIs
Publication statusPublished - 13 Feb 2017

Keywords

  • aeroelasticity
  • nonlinear
  • ROM
  • POD
  • DEIM
  • Reduced order model
  • Limit Cycle Oscillations

ASJC Scopus subject areas

  • Aerospace Engineering
  • Modelling and Simulation

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