Structure of a double-fin turbulent interaction at high speed

Abstract

This study examines the interaction of a Mach 8.3 turbulent boundary layer with intersecting oblique shock waves generated by 15-deg sharp fins mounted symmetrically on a flat plate. The full three-dimensional massaveraged compressible Navier-Stokes equations are solved with a high-resolution implicit finite-volume scheme. Turbulence closure is achieved with variations of the Baldwin-Lomax algebraic model. Excellent agreement with experimental data is observed for plate surface pressure. However, accurate heat transfer rates are obtained only near the plane of symmetry. Some quantitative details are dependent on the manner in which the turbulence model is implemented. Within this limitation, the overall computed mean flow structure remains similar and mesh independent and compares well with available field surveys. The incoming flat plate boundary layer separates along the entire spanwise width and does not reattach in the domain of computation. Beneath the separated boundary layer are a vortex interaction with an off-surface stagnation point, a centerline longitudinal vortex, and an entrainment flow originating from the essentially inviscid stream near the fin leading edge.

Progress in shock wave/boundary layer interactions

“…Some of the main evidence for this assertion is shown in Fig. 5 for the double fin configuration [77,78]. Frame (a) shows surface oil flow patterns, which represent the footprint of the 3-D flow field for a Mach 4 flow.…”

Advances in CFD prediction of shock wave turbulent boundary layer interactions

“…Since that time, interest in this problem has greatly increased due to its relationship to scramjet propulsion since the crossing shock interaction constitutes a geometrical simplification of a hypersonic sidewall compression inlet. Symmetric interactions (i.e., α 1 = α 2 ) have been studied by [6,159,164,168,169,170,171,172,173,174,175,176,177,178,179,180,181,182,183,184,185,186,187,188,189,190,191,192,193,194,195,196,197,198,199,200,201,202,203,204,205,206,207,208,209]. Asymmetrical interactions (i.e., α 1 = α 2 ) have been studied by [6,164,167,…”

“…The calculations conducted for symmetrical [159,164,170,174,175,176,177,180,181,182,183,184,186,188,189,190,191,192,193,199,200,201,202,203,204,205,206,208,209,210,213,214] and asymmetrical [164,187,192,193,197,199,202,203,204,208,209,211,212,213,214,215,216,218] interactions and for symmetrical fins mounted on the compression surface [190,219]. As it follows from review of investigations of the flow for symmetrical and asymmetrical intera...…”

Numerical Investigation of Strong Crossing Shock-Wave/Turbulent Boundary-Layer Interactions

“…Because the surface pattern of the 18 £ 18 deg interaction is generally similar to that reported in earlier efforts, 3 it is not discussed in detail. The principal new features are the appearance of tertiary separation and attachmentfeatures in the form of R 3 and S 3 (Fig.…”

“…The starting point for the present analysis lies in the three-dimensional model proposed by Gaitonde et al in a series of papers. 3 7 For strong (or fully separated) interactions the principal elements of the ow are described in terms of four ow regimes 3 : the separated boundary layer, vortex interaction,centerline vortices, and entrainment.Each regime has a distinct"footprint,"and the lines of coalescenceand divergencethat mark the boundariesbetween the various regimes will be discussed in more detail in a later section.…”