Trailing-Edge Flows at High Reynolds Number

Viswanath, P.; Cleary, J. W.; Seegmiller, H. L.; Horstman, C. C.

doi:10.2514/3.50854

Cited by 12 publications

(5 citation statements)

References 8 publications

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“…The profile has a classical shape common to free turbulent shear flows, e.g. wakes, [2,7,8,10,11,12] and jets [25].…”

Section: Bow Shocksmentioning

confidence: 99%

“…Orloff and Olson's [7] study of the low-speed flow about a flapped airfoil focused mainly on the experimental technique. Viswanath et al [8] investigated the compressible wake of an isolated airfoil using laser doppler anemometry (LDA). A salient finding therein was that the shear stress profiles were "frozen" or constant with streamwise location in the near wake.…”

Section: Introductionmentioning

confidence: 99%

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Turbulence Characteristics in a Supersonic Cascade Wake Flow

Andrew

1993

Volume 3C: General

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The turbulent character of the supersonic wake of a linear cascade of fan airfoils has been studied using a two–component Laser Doppler Anemometer. The cascade was tested in the Virginia Polytechnic Institute and State University intermittent wind tunnel facility, where the Mach and Reynolds numbers were 2.36 and 4.8 × 106, respectively. In addition to mean flow measurements, Reynolds normal and shear stresses were measured as functions of cascade incidence angle and streamwise locations spanning the near–wake and the far–wake. The extremities of profiles of both the mean and turbulent wake properties were found to be strongly influenced by upstream shock–boundary–layer–interactions, the strength of which varied with cascade incidence. In contrast, the peak levels of turbulence properties within the shear layer were found to be largely independent of incidence, and could be characterized in terms of the streamwise position only. The velocity defect turbulence level was found to be 23%, and the generally–accepted value of the turbulence structural coefficient of 0.30 was found to be valid for this flow. The degree of similarity of the mean flow wake profiles was established, and those profiles demonstrating the most similarity were found to approach a state of equilibrium between the mean and turbulent properties. In general, this wake flow may be described as a classical free shear flow, upon which the influence of upstream shock–boundary–layer–interactions has been superimposed.

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“…The profile has a classical shape common to free turbulent shear flows, e.g. wakes, [2,7,8,10,11,12] and jets [25].…”

Section: Bow Shocksmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Turbulence Characteristics in a Supersonic Cascade Wake Flow

Andrew

1993

Volume 3C: General

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“…The flows in Refs. 2 and 3 also recover to a plane mixing layer but at much greater distances from the trailing edge; for example, the double-peak intensity profiles of the present flow reduces to a single-peak profile at x/c = 0.07, while for 16 arrow in the figure) and again implies nonequilibrium behavior. The shear stress on the suction side increases due to the combined influence of adverse pressure gradient and destabilizing streamline curvature.…”

Section: Reynolds Stressesmentioning

confidence: 70%

“…A number of studies have been reported on the flow around the trailing edge of a flat plate 4 " 9 and a symmetric aerofoil, 10 " 14 and recently Nakayama 15 and Viswanath et al 16 have investigated the flow in the trailing edge region of an asymmetric aerofoil. In Ref.…”

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confidence: 98%

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Flow over a trailing flap and its asymmetric wake

1987

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Detailed measurements of pressure and velocity characteristics are reported for the attached flow on a trailing flap and in its downstream asymmetric wake. The results indicate that the flow over the flap is subjected to an adverse pressure gradient. Near the trailing edge, an inflection point develops in the streamwise velocity profile and the flow approaches intermittent separation. The wake is asymmetric with a destabilizing curvature on the suction side and a stabilizing curvature on the pressure side. Streamwise variations in the near wake are primarily confined to the inner layer, and further downstream the mean velocity and turbulence quantities attain selfsimilar profiles. Nonequilibrium effects are present in the near wake and imply that mixing length models are not appropriate. Both the pressure gradient term and the cross-stream gradient of the turbulent stresses are found to be important. Streamwise gradients of the turbulent stresses are, however, small. Nomenclatureb = width of the upper part (y/d>0) of the wake B = constant in the law of the wall equation c = chord length (Fig. 1) c p -pressure coefficient c pw = pressure coefficient along the flap surface c poo = freestream pressure coefficient k = constant in the law of the wall equation l p= distance from the wake center to the point where the streamwise velocity defect in the pressure side is half the maximum defect / 5 = distance from the wake center to the point where the streamwise velocity defect in the suction side is half the maximum defect L = mixing length n = normal distance from the flap surface p = pressure q = kinetic energy of turbulence s = distance along the surface measured from the trip wire ii, u' = mean and fluctuating velocity in the streamwise __ direction u'v' -mean shear stress u' 2 =mean normal stress in the streamwise direction u c = mean streamwise velocity at wake center ii eu = mean streamwise velocity in the suction-side freestream u el = mean streamwise velocity in the pressure-side freestream H ref = mean reference velocity in the streamwise direction v,v' = mean and fluctuating cross-stream velocity v' 2 = mean normal stress in the cross-stream direction w' 2 =mean normal stress in the spanwise direction Xt y = streamwise coordinate in the wake measured from the trailing edge, and cross-stream coordinate <5 = boundary-layer thickness, i.e., the distance from the wall where the velocity reaches 99.5% of the freestream velocity

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Laser Velocimetry for Transonic Aerodynamics

Johnson

1986

Recent Advances in Aerodynamics

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Trailing-Edge Flows at High Reynolds Number

Cited by 12 publications

References 8 publications

Turbulence Characteristics in a Supersonic Cascade Wake Flow

Turbulence Characteristics in a Supersonic Cascade Wake Flow

Flow over a trailing flap and its asymmetric wake

Laser Velocimetry for Transonic Aerodynamics

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