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.
|Title of host publication||Proceedings for Royal Aeronautical Society 5th Aircraft Structural Design Conference|
|Publisher||Royal Aeronautical Society|
|Number of pages||16|
|Publication status||Published - 01 Nov 2016|
|Event||Royal Aeronautical Society 5th Aircraft Structural Design Conference - Manchester Conference Centre, Manchester, United Kingdom|
Duration: 04 Oct 2016 → 06 Oct 2016
http://www.aerosociety.com/Events/Event-List/1980/5th-Aircraft-Structural-Design-Conference (Link to event details online)
|Conference||Royal Aeronautical Society 5th Aircraft Structural Design Conference|
|Period||04/10/2016 → 06/10/2016|
ASJC Scopus subject areas
- Aerospace Engineering
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.