Near-Wall Measurements of a Three-Dimensional Turbulent Boundary Layer.

Compton, Debora A.; Eaton, John K.

doi:10.21236/ada344017

Cited by 7 publications

(11 citation statements)

References 43 publications

(60 reference statements)

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“…All tests were conducted in the Stanford Flow Control Wind Tunnel. Details regarding the tunnel are given in Compton (1995). This was a recirculating wind tunnel with a maximum velocity in the test section of 22 m/s, very good flow uniformity, and freestream turbulence intensities less than 0.5%.…”

Section: Wind Tunnelmentioning

confidence: 99%

Wake Vortex Alleviation Using Rapidly Actuated Segmented Gurney Flaps

Matalanis

Eaton

2007

AIAA Journal

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Section: Wind Tunnelmentioning

confidence: 99%

Wake Vortex Alleviation Using Rapidly Actuated Segmented Gurney Flaps

Matalanis

Eaton

2007

AIAA Journal

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“…All three profiles collapse onto one line in the near-wall region. This is also more or less the case for the measurements of Compton & Eaton (1995) but not for those ofÖlçmen & Simpson (1996) where γ τ lags γ g . The profiles at stations 10U and 10D are characteristic of cross-over behaviour and all three angles change sign twice.…”

Section: Characteristic Flow Anglesmentioning

confidence: 87%

“…Klinksiek & Pierce (1970) measured mean velocity profiles with two-sided lateral skewing in an 'S'-shaped channel of rectangular crosssection and Webster, DeGraaff & Eaton (1996) in a boundary layer over a swept bump. Recent measurements were performed by Schwarz & Bradshaw (1992, 1994 and by Compton & Eaton (1995) in a curved duct with unilaterally skewed velocity profiles and byÖlçmen & Simpson (1995b), in the flow of a wing-body junction.…”

Section: Introductionmentioning

confidence: 99%

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An experimental investigation of a three-dimensional turbulent boundary layer in an ‘S’-shaped duct

1999

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This paper describes the evolution of an incompressible turbulent boundary layer on the flat wall of an ‘S’-shaped wind tunnel test section under the influence of changing streamwise and spanwise pressure gradients. The unit Reynolds number based on the mean velocity at the entrance of the test section was fixed to 106 m−1, resulting in Reynolds numbers Reδ2, based on the streamwise momentum thickness and the local freestream velocity, between 3.9 and 11 × 103. The particular feature of the experiment is the succession of two opposite changes of core flow direction which causes a sign change of the spanwise pressure gradient accompanied by a reversal of the spanwise velocity component near the wall, i.e. by the formation of so-called cross-over velocity profiles. The aim of the study is to provide new insight into the development of the mean and fluctuating flow field in three-dimensional pressure-driven boundary layers, in particular of the turbulence structure of the near-wall and the cross-over region.Mean velocities, Reynolds stresses and all triple correlations were measured with a newly developed miniature triple-hot-wire probe and a near-wall hot-wire probe which could be rotated and traversed through the test plate. Skin friction measurements were mostly performed with a wall hot-wire probe. The data from single normal wires extend over wall distances of y+ [gsim ] 3 (in wall units), while the triple-wire probe covers the range y+ [gsim ] 30. The data show the behaviour of the mean flow angle near the wall to vary all the way to the wall. Then, to interpret the response of the turbulence to the pressure field, the relevant terms in the Reynolds stress transport equations are evaluated. Finally, an attempt is made to assess the departure of the Reynolds stress profiles from local equilibrium near the wall.

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“…The elliptical leading edge of the flat plate (plate a) has a fineness ratio of 0.3 as typically found for low-speed boundary layer investigations. [18][19][20][21] The EMFC device is located between the two filler plates labeled c. Additionally, a trailing edge plate d completes the assembly.…”

Section: Low Speed Facility Design Considerationsmentioning

confidence: 99%

Electromagnetic Boundary Layer Flow Control Facility Development Using Conductive Particle Seeding

Braun

Mitchell

Nozawa

et al. 2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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A facility for electromagnetic boundary layer flow control employing conductive particle seeding is in the initial stages of development, fabrication and testing. The facility consists of three integrated components: a conductive particle seeding mechanism, an ionization plate and a Lorentz force generator plate that comprises of a series of flushmounted surface electrodes and embedded rare earth magnets. Initial bench-top testing is reported with the future intention of testing the facility in the low speed and supersonic flow regimes. An aqueous salt solution reduced the voltage required to create a corona discharge by the ionization plate. The ionization of seeded air by an electric field presents several problems, notably an increased tendency for arcing as the conductivity within the boundary layer increases. The aqueous salt solution was accelerated or decelerated by the Lorentz force generator depending on the electromagnetic configuration. The benchtests demonstrated the ability of raising the conductivity of air to enable Lorentz force actuation under normal atmospheric conditions.

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Near-Wall Measurements of a Three-Dimensional Turbulent Boundary Layer.

Cited by 7 publications

References 43 publications

Wake Vortex Alleviation Using Rapidly Actuated Segmented Gurney Flaps

Wake Vortex Alleviation Using Rapidly Actuated Segmented Gurney Flaps

An experimental investigation of a three-dimensional turbulent boundary layer in an ‘S’-shaped duct

Electromagnetic Boundary Layer Flow Control Facility Development Using Conductive Particle Seeding

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