Vortex velocity distributions at large downstream distances.

Logan, A. H.

doi:10.2514/3.44313

Cited by 20 publications

(4 citation statements)

References 1 publication

(1 reference statement)

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“…The laminar profile appears correct at up to 1 • 5 x core radius, but the experimental data agree best at all radii with the turbulent vortex theory with the parameter (27rv/aT (x ) taking a value of the order of 5. Logan's velocity profiles (Ref 18). are also consistent with that value of the parameter.…”

supporting

confidence: 64%

The static pressure in a vortex core

Dunham

1979

Aeronaut. j.

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Vortices are of interest in many situations in fluid mechanics. One type of vortex with which the gas turbine designer is concerned is the line vortex springing like a miniature tornado from a point on the ground (or from a nearby aircraft surface) and entering the engine intake. It is possible for these vortices to suck stones up into the engine (Refs. 1, 2) and also to reduce the compressor surge margin (Refs. 3, 4). They are unsteady, in that their point of origin wanders about and so does their point of entry into the intake. This unsteadiness makes it very difficult to measure them, and so far no one known to the author has reported measurements of ground vortex strength, in the course of several investigations of the phenomenon (Refs. 1-3, 5-8).

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supporting

confidence: 64%

The static pressure in a vortex core

Dunham

1979

Aeronaut. j.

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“…1.2.11 can give an axial velocity excess or deficit at the outer edge of the viscous core. Comparisons with available experimental data are poor although the measurements of Logan (1971) showed a qualitatively similar axial flow, with a velocity deficit at the centerline and an axial velocity excess at the edge of the viscous core. The radius of the core (whose edge was defined as the point of maximum tangential velocity) for an elliptically loaded wing was found to be:…”

Section: Analysis Of Laminar Vorticesmentioning

confidence: 87%

Mean and Turbulence Measurements in the Near Field of a Wingtip Vortex

1997

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“…Profiles of axial velocity have been reported by Logan (1971). These are compared in table 1 with the theoretical prediction of (4.4).…”

Section: Discussionmentioning

confidence: 99%

Axial flow in laminar trailing vortices

Moore

Saffman

1973

Proc. R. Soc. Lond. A

141

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The structure of laminar trailing vortices behind a lifting wing is considered. The inviscid roll up of the trailing vortex sheet is examined, and the nature of the singularity at the centre of the spiral is determined. It is shown that viscosity removes the singularity and the structure of the viscous core is obtained. The pressure in the viscous core is found and used to calculate the axial velocities produced by streamwise pressure gradients. It is found that the perturbation of axial velocity can be either away from the wing or towards the wing depending on the distribution of tip loading on the wing. For elliptic loading, the perturbation is towards the wing. The axial flow deficit in the core due to the boundary layers on the wing is also estimated. A comparison with experiment is made and reasonable agreement is found.

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Vortex velocity distributions at large downstream distances.

Cited by 20 publications

References 1 publication

The static pressure in a vortex core

The static pressure in a vortex core

Mean and Turbulence Measurements in the Near Field of a Wingtip Vortex

Axial flow in laminar trailing vortices

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