INVESTIGADORES
ELASKAR sergio Amado
artículos
Título:
Open FOAM simulations of the supersonic flow around cones at angles of attack
Autor/es:
LORENZÓN, DENIS; ELASKAR, SERGIO
Revista:
Journal of Mechanical and Civil Engineering
Editorial:
IOSR Journals
Referencias:
Año: 2019 vol. 16 p. 66 - 80
ISSN:
2320-334X
Resumen:
The supersonic flow around conical bodies is a very important issue in aerospace engineering, with many applications in internal and external supersonic aerodynamics. Non-viscous supersonic flow about yawing cones is essentially 3-dimensional, but it shows some characteristics regarding the conical flow around circular cones with zero angle of attack. In this latter case, the complete flow structure is axisymmetric and can be described by an ordinary differential equation known as the Taylor-Maccoll equation. When the angle of attack is non-zero, the flow is still conical, i.e., the properties are constant over straight lines passing through the vertex (they are independent of the radial coordinate r , even though they depend on the polar θ and azimuthal φ coordinates. This kind of flow has the following remarkable characteristics: a) the shock wave angle depends on the meridian angle, i.e., σ = σ ( φ ) , b) the streamlines between the shock and the conesurface are curved in three dimensions, c) the flow between the cone and the shock wave exhibits entropic gradients perpendicular to the streamlines which makes it rotational, d) in the vertical plane, there exists a radial line on which converge streamlines with different entropy, called vorticity singularity. If the angle of attack is smaller or larger than the cone's half-angle, this vorticity singularity will be attached to the upper surface of the body or separated above it, respectively, e) as the relation between the angle of attack and the aperture angle increases, the cross flow velocity can become supersonic and embedded (or internal) shock waves may appear. Experimental measurements show that the windward flow is accurately described by the non-viscous analysis, however the leeward region is characterized by flow separation. Associated with this flow separation there come up primary and secondary vortices, and if the cross flow velocity is supersonic, two pairs of internal shock waves will appear produced by the sudden change in the flow direction in the separation zone. In this paper we analyze the abilities of the rhoCentralFoam solver of the OpenFOAM suite for the numerical simulation of these flows, using a grid which is coarse enough to be run in a desktop computer. The main objective is to describe the 3D features of the supersonic flow around yawing cones using a modern software, like OpenFOAM, without the need for a computing cluster.