Near-wall Similarity in Three-dimensional Turbulent Boundary Layers PDF Download
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Author: Mark Harris Tennant
Publisher:
ISBN:
Category :
Languages : en
Pages : 786
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Book Description
Author: Mark Harris Tennant
Publisher:
ISBN:
Category :
Languages : en
Pages : 786
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Book Description
Author: John E. McAllister
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 1490
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Book Description
Author: O. Sendstad
Publisher:
ISBN:
Category : Simulation methods
Languages : en
Pages : 130
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Book Description
Author: Stanford University. Thermosciences Division. Thermosciences Division
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
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Book Description
Author: Olav Sendstad
Publisher:
ISBN:
Category :
Languages : en
Pages : 146
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Book Description
Author: Arthur G. Hansen
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 716
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Book Description
Solutions of mainstream flow patterns for all possible incompressible laminar-boundary-layer flows having classical similarity with respect to rectangular coordinate systems are derived. These solutions, which apply to a wide range of flows, are summarized in table form.
Author: J. P. Johnston
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 62
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Book Description
The various methods for measurement of the six components of the turbulence stress tensor are reviewed, and some of the data on the turbulent shear stress vector are presented to demonstrate the validity of current ideas for.
Author: Debora Alice Compton
Publisher:
ISBN:
Category :
Languages : en
Pages : 222
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Book Description
In order to improve predictions of flow behavior in numerous applications there is a great need to understand the physics of three-dimensional turbulent boundary layers, dominated by near-wall behavior. To that end, an experiment was performed to measure near-wall velocity and Reynolds stress profiles in a pressure-driven three-dimensional turbulent boundary layer. The flow was achieved by placing a 30 deg wedge in a straight duct in a wind tunnel, with-additional pressure gradient control above the test surface. An initially two-dimensional boundary layer (Re approx. equal 4000) was exposed to a strong spanwise pressure gradient. At the furthest downstream measurement locations there was also a fairly strong favorable pressure gradient. Measurements were made using a specially-designed near-wall laser Doppler anemometer (LDA), in addition to conventional methods. The LDA used short focal length optics, a mirror probe suspended in the flow, and side-scatter collection to achieve a nearly spherical measuring volume approximately 35 microns in diameter. Good agreement with previous two-dimensional boundary layer data was achieved. The three-dimensional turbulent boundary layer data presented include mean velocity measurements and Reynolds stresses, all extending well below y(+) = 10, at several profile locations. Terms of the Reynolds stress transport equations are calculated at two profile locations. The mean flow is nearly collateral at the wall. Turbulent kinetic energy is mildly suppressed in the near-wall region and the shear stress components are strongly affected by three-dimensionality. As a result, the ratio of shear stress to turbulent kinetic energy is suppressed throughout most of the boundary layer. The angles of stress and strain are misaligned, except very near the wall (around y(+) = 10) where the angles nearly coincide with the mean flow angle.
Author: A.T. Degani
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Kattinger Sheshagiri Hebbar
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 178
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Book Description
An experimental investigation was conducted at selected locations of the near-wall region of a three-dimensional turbulent air boundary layer relaxing in a nominally zero external pressure gradient behind a transverse hump (in the form of a 30 degree swept, 5-foot chord wing-type model) faired into the side wall of a low speed wind tunnel. Wall shear stresses measured with a flush-mounted hot-film gage and a sublayer fence were in very good agreement with experimental data obtained with two Preston probes. With the upstream unit Reynolds number held constant at 325000/ft approximately one-fourth of the boundary layer thickness adjacent to the wall was surveyed with a single rotated hot-wire probe mounted on a specially designed minimum interference traverse mechanism. The boundary layer (approximately 3.5 in. thick near the first survey station where the length Reynolds number was 5500000) had a maximum crossflow velocity ratio of 0.145 and a maximum crossflow angle of 21.875 degrees close to the wall. The hot-wire data indicated, in agreement with the findings elsewhere, that the apparent dimensionless velocity profiles in the viscous sublayer region are universal and that the wall influence is negligible beyond y(+) =5. The existence of wall similarity in the relaxing flow field was confirmed in the form of a log law based on the resultant mean velocity and resultant friction velocity (obtained from measured skin friction).
