Turbulent boundary-layer growth and separation on a yawed cone.

Rainbird, W. J.

doi:10.2514/3.5002

Cited by 71 publications

(6 citation statements)

References 2 publications

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“…For both cones, the effects of flow separation become appreciable when /3 > 1.1 in good agreement with experimental data. 2 -3 ' 15 At lower values of f3 an irregular vortex sheet develops remaining very close to the body surface and resembling a vortex bubble more than a vortex sheet.…”

Section: Resultsmentioning

confidence: 98%

“…However, the results of Rainbird's recent tests on a 12.5° cone under turbulent boundary-layer separation have indicated that the separation angle is a function of relative incidence, and that the flow features were "qualitatively similar" to laminar boundary-layer separation at low speeds. 15 The differences between the results of Refs. 16 and 17 may be in part explained by the use of different criteria assumed in the definition of the separation angle.…”

Section: Separation Pointsmentioning

confidence: 83%

“…2 ' 3 ' 15 The most significant results of such investigations are summarized here. Both for laminar and for turbulent separation, the axial point of separation x s is located at the cone tip; incipient vortex separation starts at a relative incidence ft of about 0.8, although no appreciable vortex effects are experienced Until ft ^ 1.0 to 1.1.…”

Section: Separation Pointsmentioning

confidence: 98%

“…Equation (13) The last term of the right side of Eq. (15), that is, the absolute value of the velocity induced by the discrete vortices will be later identified simply by…”

Section: Kutta Conditionmentioning

confidence: 99%

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A multivortex method for axisymmetric bodies at angle of attack.

Angelucci

1971

Journal of Aircraft

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A multivortex model made up of a large number of discrete free vortices has been used to represent the actual vortex sheets shed from the lee side of a slender body at an angle of attack. Circulation, strength, and position of the vortices, together with the induced normal forces, are evaluated at various axial positions along the body axis. The viscous inputs to the analysis are the separation or feeding points which are provided by experiment or semi-empirical theories. A discussion of the numerical computations and a comparison with experimental data are presented.n Re y r Nomenclature body axes d/2 -base or reference radius A r /(0-5p co 1 T 00 2 7ra 2 ) = normal force coefficient MApcoFooVa 3 ) = pitching moment coefficient vortex induced normal force and pitching moment coefficients x = local normal force coefficient sin 2 c*a) = cross-flow drag coefficient total impulse body total length Mach number number of vortices Reynolds number body local radius nondimensional length of the vortex sheet length measured along the vortex sheet from point of separation time frees tream velocity u + iv -complex velocity in the cross-flow plane nondimensional velocities, u' = u/V^ . . . angle of attack relative incidence, /? = tana/tane circulation per unit length of the vortex sheet circulation strength of vortex sheet or discrete vortex semi apex angle of the cone r/27rF 00 r 0 = nondimensional circulation strength, also X' = Xr 0 /a air density £ + it]] a -% -it] -complex coordinate, also or = re id ; a = re~i e + i\I/ = complex velocity potential (or potential function) velocity potential angular orientation of the vortex sheet at the center of vorticity

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Section: Resultsmentioning

confidence: 98%

Section: Separation Pointsmentioning

confidence: 83%

Section: Separation Pointsmentioning

confidence: 98%

“…Equation (13) The last term of the right side of Eq. (15), that is, the absolute value of the velocity induced by the discrete vortices will be later identified simply by…”

Section: Kutta Conditionmentioning

confidence: 99%

See 2 more Smart Citations

A multivortex method for axisymmetric bodies at angle of attack.

Angelucci

1971

Journal of Aircraft

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“…Numerical resolution and turbulence modeling both become important. To illustrate the effect of the choice of turbulence model, the data from the bench mark flow published by Rainbird (1968) at a given axial location are compared with several computations in figure 31. The surface shear-stress angle direc t ions ws are defined relative to the conical generator.…”

Section: Cross-flow Separation At Supersonic Speedsmentioning

confidence: 99%