Reduced order modeling of three dimensional external aerodynamic flows

Vega De Prada, Jose Manuel; Alonso, D.; Velázquez, Angel y Pablo, Valentín de (2012). Reduced order modeling of three dimensional external aerodynamic flows. "Journal of Aerospace Engineering", v. 25 (n. 4); pp. 588-599. ISSN 0893-1321. https://doi.org/10.1061/(ASCE)AS.1943-5525.0000148.

Descripción

Título: Reduced order modeling of three dimensional external aerodynamic flows
Autor/es:
  • Vega De Prada, Jose Manuel
  • Alonso, D.
  • Velázquez, Angel
  • Pablo, Valentín de
Tipo de Documento: Artículo
Título de Revista/Publicación: Journal of Aerospace Engineering
Fecha: Junio 2012
Volumen: 25
Materias:
Escuela: E.T.S.I. Aeronáuticos (UPM) [antigua denominación]
Departamento: Fundamentos Matemáticos de la Tecnología Aeronáutica [hasta 2014]
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

A method is presented to construct computationally efficient reduced-order models (ROMs) of three-dimensional aerodynamic flows around commercial aircraft components. The method is based on the proper orthogonal decomposition (POD) of a set of steady snapshots, which are calculated using an industrial solver based on some Reynolds averaged Navier-Stokes (RANS) equations. The POD-mode amplitudes are calculated by minimizing a residual defined from the Euler equations, even though the snapshots themselves are calculated from viscous equations. This makes the ROM independent of the peculiarities of the solver used to calculate the snapshots. Also, both the POD modes and the residual are calculated using points in the computational mesh that are concentrated in a close vicinity of the aircraft, which constitute a much smaller number than the total number of mesh points. Despite these simplifications, the method provides quite good approximations of the flow variables distributions in the whole computational domain, including the boundary layer attached to the aircraft surface and the wake. Thus, the method is both robust and computationally efficient, which is checked considering the aerodynamic flow around a horizontal tail plane, in the transonic range 0.4?Mach number?0.8, ?3°?angle of attack?3°.

Más información

ID de Registro: 15415
Identificador DC: http://oa.upm.es/15415/
Identificador OAI: oai:oa.upm.es:15415
Identificador DOI: 10.1061/(ASCE)AS.1943-5525.0000148
URL Oficial: http://ascelibrary.org/doi/abs/10.1061/%28ASCE%29AS.1943-5525.0000148?journalCode=jaeeez
Depositado por: Memoria Investigacion
Depositado el: 21 Abr 2015 10:24
Ultima Modificación: 21 Abr 2015 10:24
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