Global Stability Analysis of a Compressible Turbulent Flow around a High-Lift Configuration

Iorio, Maria Chiara and Gonzalez, Leo M. and Martinez Cava, Alejandro (2015). Global Stability Analysis of a Compressible Turbulent Flow around a High-Lift Configuration. In: "45th AIAA Fluid Dynamics Conference", 22-26 June 2015, Dallas, Texas, USA. pp. 1-25.

Description

Title: Global Stability Analysis of a Compressible Turbulent Flow around a High-Lift Configuration
Author/s:
  • Iorio, Maria Chiara
  • Gonzalez, Leo M.
  • Martinez Cava, Alejandro
Item Type: Presentation at Congress or Conference (Article)
Event Title: 45th AIAA Fluid Dynamics Conference
Event Dates: 22-26 June 2015
Event Location: Dallas, Texas, USA
Title of Book: AIAA 2015-2636
Date: 2015
Subjects:
Faculty: E.T.S. de Ingeniería Aeronáutica y del Espacio (UPM)
Department: Otro
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

The purpose of this work is to analyze a complex high lift configuration for which significant regions of separated flow are present. Current state of the art methods have some diffculty to predict the origin and the progression of this separated flow when increasing the angle of attack. The mechanisms responsible for the maximum lift limit on multi-element wing con?gurations are not clear; this stability analysis could help to understand the physics behind the phenomenon and to find a relation between the flow separation and the instability onset. The methodology presented herein consists in the computation of a steady base flow solution based on a finite volume discretization and a proposal of the solution for a generalized eigenvalue problem corresponding to the perturbed and linearized problem. The eigenvalue problem has been solved with the Arnoldi iterative method, one of the Krylov subspace projection methods. The described methodology was applied to the NACA0012 test case in subsonic and in transonic conditions and, finally, for the first time to the authors knowledge, on an industrial multi-component geometry, such as the A310 airfoil, in order to identify low frequency instabilities related to the separation. One important conclusion is that for all the analyzed geometries, one unstable mode related to flow separation appears for an angle of attack greater than the one correspondent to the maximum lift coe?cient condition. Finally, an adjoint study was carried out in order to evaluate the receptivity and the structural sensitivity of the geometries, giving an indication of the domain region that could be modified resulting in the biggest change of the flowfield.

Funding Projects

TypeCodeAcronymLeaderTitle
Government of SpainTRA2010-16988UnspecifiedUnspecifiedCaracterizaci�on Num�erica y Experimental de las Cargas Fluido-Din�amicas en el transporte de Gas Licuado

More information

Item ID: 38031
DC Identifier: http://oa.upm.es/38031/
OAI Identifier: oai:oa.upm.es:38031
Official URL: http://arc.aiaa.org/doi/abs/10.2514/6.2015-2636
Deposited by: Memoria Investigacion
Deposited on: 12 Feb 2016 20:34
Last Modified: 12 Feb 2016 20:34
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