The Structure of Three-Dimensional Separated Flows in Obstacle-Boundary Layer Interactions.

Sedney, Raymond; Kitchens, Clarence W.

doi:10.21236/ada011254

Cited by 34 publications

(14 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…We were successful in demonstrating the usefulness of a hypothesis that the skin friction lines on the surface are said to behave as a continuous vector field and the singular points in this field obey the topological 7,8 rule This verification also confirmed the primary separation line and horseshoe vortex structure for the surface mounted 9 obstacle, boundary layer interaction…”

Section: Introductionsupporting

confidence: 53%

Effect of suction on the wake structure of a three-dimensional turret

Purohit

1983

16th Fluid and Plasmadynamics Conference

View full text Add to dashboard Cite

Section: Introductionsupporting

confidence: 53%

Effect of suction on the wake structure of a three-dimensional turret

Purohit

1983

16th Fluid and Plasmadynamics Conference

View full text Add to dashboard Cite

“…The skin-friction line pattern shown here is the same as that of the classical four vortex system (two primary and two secondary vortices) shown by Sedney and Kitchens. 4 However, there are only three vortices seen on the plane of symmetry in Figs. 3 and 4.…”

Section: B Laminar Juncture Flow For Various Mach Numbersmentioning

confidence: 95%

“…The experimental work was done by Sedney and Kitchens. 4 The turbulence model used in the computation is a modified BaldwinLomax model 13 backflow regions. For multiple surfaces, the eddy viscosity is blended using a distance function: \i t = (\L\/d\ + /* 2 /tf 2 )/ Vl/t/f + 1/t/l where d\ and d 2 are the distances measured from the flat plate and the cylinder.…”

Section: Supersonic Turbulent Juncture Flowmentioning

confidence: 99%

Numerical study of juncture flows

Chen¹,

Hung

1992

AIAA Journal

View full text Add to dashboard Cite

A computational study of laminar/turbulent and subsonic/supersonic horseshoe vortex systems generated by a cylindrical protuberance mounted on a flat plate is presented. Various vortex structures have been predicted and are discussed. For a low subsonic laminar flow, the number of computed vortex arrays increases with Reynolds number (with fixed incoming boundary-layer thickness), in agreement with experimental and previous numerical observations. The relationships among pressure extrema, vorticity, and the singular points in the flow structure on the plane of symmetry over the flat plate are studied. Mach number effects have also been investigated for laminar flow at one Reynolds number. The outermost singular point moves upstream when freestream Mach number increases. The size of the whole vortex structure increases dramatically due to shock-wave/boundary-layer interaction. The computed laminar horseshoe vortex systems start from a saddle point of attachment. In the case of a supersonic turbulent flow at a high Reynolds number, the computed results predict the same features as those indicated by the experimental results, such as the upstream shock-wave/ boundary-layer interaction and the classical horseshoe vortex system starting from a saddle point of separation. The calculations provide details of the downstream wake/shock-wave interaction and the near wake tornadolike vortex structure. The overall flow topology is discussed. Nomenclaturemeasured from the flat plate and cylinder E = extremum of p(x) H = height or semiheight of cylinder (clear from context) MOO = freestream Mach number N, N' = node and half-node, respectively p = pressure Re D = Reynolds number based on cylinder diameter S = saddle or separation (clear from context) S'-half-saddle u = velocity component in x direction x, y, z = Cartesian coordinates (origin is at center of cylinder) 6, = incoming boundary-layer thickness <5= cylinder-location boundary-layer thickness £, ry = vorticity components in x, y directions 9 = angle of separation or attachment IJL, IJL ( = molecular and turbulence eddy viscosity

show abstract

“…images, have facilitated thorough understanding of complex flow phenomena (Couch, 1969;Hiers and Loubsky, 1967;Kaufman et al, 1973;Sedney, 1973Sedney, , 1975Waltrup et al, 1968;Westkaemper, 1968;Whitehead, 1969). However, few experimental studies exist concerning heat transfer around the protuberances caused by aerodynamic heating (Hung and Clauss, 1980;Hung and Patel, 1984;Truitt, 1965); in addition, the quality of the data is limited.…”

mentioning

confidence: 99%

“…However, few experimental studies exist concerning heat transfer around the protuberances caused by aerodynamic heating (Hung and Clauss, 1980;Hung and Patel, 1984;Truitt, 1965); in addition, the quality of the data is limited. In recent studies, Lee et al (2009) examined aerodynamic heating characteristics near the vicinity of the protuberance from measurements acquired from heat flux sensors, such as a Gordon gauge through the blow down hypersonic wind tunnel testing under a Mach number of 7.…”

mentioning

confidence: 99%