E.T.S.I. Aeronauticos

Madrid, Spain

E.T.S.I. Aeronauticos

Madrid, Spain
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Carpio J.,Technical University of Madrid | Linan A.,E.T.S.I. Aeronauticos | Sanchez A.L.,University of California at San Diego | Williams F.A.,University of California at San Diego
Combustion and Flame | Year: 2017

The laminar flow resulting from impingement of two steadily fed low-Mach-number gaseous jets issuing into a stagnant atmosphere from coaxial cylindrical ducts at moderately large Reynolds numbers, often used in combustion experiments, is studied through numerical integrations of the Navier–Stokes equations. In the Reynolds-number range addressed, 50–1000, the flow of the approaching jets is nearly inviscid, with viscous effects and mixing being restricted to the thin mixing layers surrounding the jets and to a thin layer located at the separating stream surface. The analysis of the main inviscid flow shows that only two parameters, based on the scales associated with the radius and the velocity profiles of the two feed streams, are needed to characterize the flow, namely, the ratio of the inter-jet separation distance to the duct radius and the ratio of momentum fluxes of the jets. The numerical results for uniform and Poiseuille velocity profiles provide, in particular, the value of the strain rate at the stagnation point for use in the analysis of experimental studies of counterflow premixed and diffusion flames. © 2016 The Combustion Institute


Fraysse F.,E.T.S.I. Aeronauticos | De Vicente J.,E.T.S.I. Aeronauticos | Valero E.,E.T.S.I. Aeronauticos
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering | Year: 2013

The aim of this article is to use an accurate truncation error estimate in order to perform τ-extrapolation and mesh adaptation in an unstructured finite volume computational fluid dynamics solver, in the context of a posteriori error estimation. The truncation error is approximated by the so-called τ-estimation technique, in which a special criterion is defined in order to account for the finite volume discretisation. It is shown that an accurate truncation error evaluation can be obtained on arbitrary geometries as long as restriction of the solution from the fine-to-coarse grid is accurate and the coarse grid possesses the same quality requirements as the fine grid. The accuracy of the truncation error estimation is successfully verified on Euler and Reynolds-averaged Navier-Stokes equations using the method of manufactured solutions. Then, mesh adaptation is performed on aerodynamic configurations where a good improvement of the force coefficients with respect to a classic feature-based indicator is obtained, at a lower cost than performing global refinement. © IMechE 2012.

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