Boundary layers and separation on a spheroid at incidence

Patel, V. C.; Baek, J. H.

doi:10.2514/3.8871

Cited by 23 publications

(7 citation statements)

References 11 publications

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“…In the preceding expression, the coefficients e (2) and e (4) are related to the pressure gradient parameter v as follows:…”

Section: Central-difference Algorithmmentioning

confidence: 99%

“…H,,= v~R e L J jV^»H (4) The equations are nondimensionalized with L*, p£, c<*, and IJL£. An ideal gas is assumed; the effect of turbulence is accounted for through the concepts of an eddy viscosity and eddy conductivity.…”

Section: Governing Equationsmentioning

confidence: 99%

“…These cases were selected because detailed experimental measurements have been made by Meier et al 1 ' 3 The measurements are extensive and include surface shear stresses, pressures, and oil flows. Previous computations are also available using boundary-layer, 4 ' 5 parabolized Navier-Stokes, 6 and thin-layer Navier-Stokes methods. 7 The primary emphasis of the present work is an assessment of the ability of the algorithms to model accurately the critical elements of the flowfield, which^ in this case, are the primary and secondary separation lines along which the vortical flows are formed.…”

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confidence: 99%

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Navier-Stokes computations of a prolate spheroid at angle of attack

Vatsa

Thomas

Wedan

1989

Journal of Aircraft

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Three-dimensional viscous flow calculations are made for a 6:1 prolate spheroid at conditions for which detailed experimental data are available. The computations are made with two finite-volume algorithms for the compressible Navier-Stokes equations, one using central differencing for the convective and pressure terms and the other using an upwind-biased flux-difference-splitting approach. The effects of artificial dissipation on the accuracy of the numerical results are included. Generally good agreement of the computations with the experimental results is obtained over a range of Reynolds numbers and angles of attack up to 30 deg, although the results at lower Reynolds numbers are sensitive to the assumed transition location.

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“…In the preceding expression, the coefficients e (2) and e (4) are related to the pressure gradient parameter v as follows:…”

Section: Central-difference Algorithmmentioning

confidence: 99%

Section: Governing Equationsmentioning

confidence: 99%

mentioning

confidence: 99%

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Navier-Stokes computations of a prolate spheroid at angle of attack

Vatsa

Thomas

Wedan

1989

Journal of Aircraft

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“…These experiments constituted several particularly well-documented test cases, including wall pressure and wall shear stress measurements as well as detailed flow probings with a multihole pressure probe. These experiments were Presented as AIAA Paper 93-3007 at the AIAA 24th Fluid Dynamics Conference, Orlando, FL, July [6][7][8][9]1993; received March 2,1994; revision received Feb. 8,1995; accepted for publication Feb. 9,1995 conducted for two incidences: 10 and 30 deg. Results were obtained for both natural and forced transition; tests at high Reynolds numbers were made in a pressurized wind tunnel.…”

Section: Cpmentioning

confidence: 99%

Experimental study of three-dimensional separation on a large-scale model

Barberis

Molton

1995

AIAA Journal

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Three-dimensional separation was studied by analyzing the flow past a large-scale model consisting of a halfprolate ellipsoid extended by a circular cylinder ending in a flat base at 45 deg with respect to the cylinder axis. The flow past the model, including boundary layer and vortical structures, was investigated in great detail using a three-component laser Doppler velocimetry system and three-hole pressure probes actuated by a displacement system installed inside the model. This last device allowed probing of the separating three-dimensional boundary layer very close to the surface. We observed how the boundary layer evolved as it gradually sheared into a vortex roll-up and then into an organized vortex. When skewing of the boundary layer increased, the difference in direction between the velocity gradient vector and the shear stress vector also increased. For this type of flow, turbulence models based on the assumption of isotropic turbulent viscosity are inadequate for numerical analysis. NomenclatureCp = static pressure coefficient L = model length Re = Reynolds number, (V Q L/v) V 1 = velocity components Vg = velocity components on the edge of the boundary layer Vq = upstream velocity at infinity X 1 = coordinates of a point on the surface a = angle of attack of the model v -kinematic viscosity (p = circumferential angle Subscripts i = 1 and 2 = components located in a plane parallel to the surface i = 3 = component normal to the surface

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“…Work in this area was essentially initiated by Wang. n~13 This was followed by contributions of Cebeci et al, 14 Patel and Baek, 15 Tai, 16 Ragab, 17 and Radwan and Lekoudis. 18 The present authors have developed an approximate method that is described in Ref.…”

Section: Introductionmentioning

confidence: 96%

Vortical wakes over a prolate spheroid

Costis

Telionis

1988

AIAA Journal

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The vortex-lattice method is employed to calculate the inviscid flow and the development of separated vortex sheets over a prolate spheroid. An approximate boundary-layer method based on the assumption of local similarity is used to calculate the line of open separation. A condition of vortex shedding along the separation line is proposed. The two methods of calculation, viscous and inviscid, interact through the line of separation that is allowed to displace as the wake grows. Results are compared with flow visualization data for laminar separation and pressure data for turbulent separation.

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Boundary layers and separation on a spheroid at incidence

Cited by 23 publications

References 11 publications

Navier-Stokes computations of a prolate spheroid at angle of attack

Navier-Stokes computations of a prolate spheroid at angle of attack

Experimental study of three-dimensional separation on a large-scale model

Vortical wakes over a prolate spheroid

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