The mode B structure of streamwise vortices in the wake of a two-dimensional blunt trailing edge

2019 ◽  
Vol 884 ◽  
Author(s):  
Bradley Gibeau ◽  
Sina Ghaemi
Keyword(s):  
Two Dimensional ◽  
Streamwise Vortices ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Image Position

Some Simple Results for Two-Dimensional Jet-Flap Aerofoils

1958 ◽  
Vol 9 (4) ◽  
pp. 395-406 ◽  
Author(s):  
D. A. Spence
Keyword(s):  
High Velocity ◽  
Lift Coefficient ◽  
Two Dimensional ◽  
Trailing Edge ◽  
Momentum Coefficient ◽  
Image Position ◽  
Derivatives Of

SummaryIt is shown from elementary considerations that the lift coefficient of a thin two-dimensional wing at zero incidence, with a narrow high-velocity jet of momentum coefficient Cj issuing from its trailing edge at a (small) downward inclination τ, is given byand the loading on the chord line (0<x<1) by(except in a certain neighbourhood of the trailing edge), for small values of Cj. These formulae agree well with known measurements. Interpolation formulae for derivatives of CL at larger values of CJ based on earlier work, are also given:

The Effect of Base Bleed on the Flow behind a Two-Dimensional Model with a Blunt Trailing Edge

1967 ◽  
Vol 18 (3) ◽  
pp. 207-224 ◽  
Author(s):  
P. W. Bearman
Keyword(s):  
Vortex Formation ◽  
Reynolds Numbers ◽  
Base Pressure ◽  
Two Dimensional ◽  
Dimensional Model ◽  
Trailing Edge ◽  
Model Base ◽  
Blunt Trailing Edge ◽  
Two Dimensional Model ◽  
Base Bleed

SummaryThe effects of base bleed on the flow about a two-dimensional model with a blunt trailing edge were examined at Reynolds numbers, based on model base height, between 1·3×104 and 4·1×104. The ratio of boundary layer thickness at the trailing edge to half the model base height was approximately 0·4. Measurements were made of base pressure, vortex shedding frequency and the distance to vortex formation. With a sufficiently large bleed quantity the regular vortex street pattern disappeared and the base drag of the section was reduced to about a third of its value without bleed. The base pressure was found to vary linearly with the inverse of the vortex formation distance. Results of a previous splitter plate investigation were found to agree closely with those of the present experiments.

On the periodically excited plane turbulent mixing layer, emanating from a jagged partition

2007 ◽  
Vol 589 ◽  
pp. 479-507 ◽  
Author(s):  
E. KIT ◽  
I. WYGNANSKI ◽  
D. FRIEDMAN ◽  
O. KRIVONOSOVA ◽  
D. ZHILENKO
Keyword(s):  
Turbulent Mixing ◽  
Mixing Layer ◽  
Two Dimensional ◽  
Streamwise Vortices ◽  
Mean Flow ◽  
Trailing Edge ◽  
Mean Velocity ◽  
Turbulent Mixing Layer ◽  
Arithmetic Average ◽  
The Mean

The flow in a turbulent mixing layer resulting from two parallel different velocity streams, that were brought together downstream of a jagged partition was investigated experimentally. The trailing edge of the partition had a short triangular ‘chevron’ shape that could also oscillate up and down at a prescribed frequency, because it was hinged to the stationary part of the partition to form a flap (fliperon). The results obtained from this excitation were compared to the traditional results obtained by oscillating a two-dimensional fliperon. Detailed measurements of the mean flow and the coherent structures, in the periodically excited and spatially developing mixing layer, and its random constituents were carried out using hot-wire anemometry and stereo particle image velocimetry.The prescribed spanwise wavelength of the chevron trailing edge generated coherent streamwise vortices while the periodic oscillation of this fliperon locked in-phase the large spanwise Kelvin–Helmholtz (K-H) rolls, therefore enabling the study of the inter- action between the two. The two-dimensional periodic excitation increases the strength of the spanwise rolls by increasing their size and their circulation, which depends on the input amplitude and frequency. The streamwise vortices generated by the jagged trailing edge distort and bend the primary K-H rolls. The present investigation endeavours to study the distortions of each mode as a consequence of their mutual interaction. Even the mean flow provides evidence for the local bulging of the large spanwise rolls because the integral width (the momentum thickness, θ), undulates along the span. The lateral location of the centre of the ensuing mixing layer (the location where the mean velocity is the arithmetic average of the two streams,y0), also suggests that these vortices are bent. Phase-locked and ensemble-averaged measurements provide more detailed information about the bending and bulging of the large eddies that ensue downstream of the oscillating chevron fliperon. The experiments were carried out at low speeds, but at sufficiently high Reynolds number to ensure naturally turbulent flow.

Drag reduction in flow over a two-dimensional bluff body with a blunt trailing edge using a new passive device

2006 ◽  
Vol 563 ◽  
pp. 389 ◽  
Author(s):  
HYUNGMIN PARK ◽  
DONGKON LEE ◽  
WOO-PYUNG JEON ◽  
SEONGHYEON HAHN ◽  
JEONGLAE KIM ◽  
...  
Keyword(s):  
Drag Reduction ◽  
Bluff Body ◽  
Two Dimensional ◽  
Trailing Edge ◽  
Passive Device ◽  
Blunt Trailing Edge

An Experimental Investigation of a Low-Speed Circulation-Controlled Aerofoil

1968 ◽  
Vol 19 (2) ◽  
pp. 170-182 ◽  
Author(s):  
R. J. Kind ◽  
D. J. Maull
Keyword(s):  
Experimental Investigation ◽  
Angle Of Incidence ◽  
Pitching Moment ◽  
Two Dimensional ◽  
Trailing Edge ◽  
Low Speed ◽  
Momentum Coefficient ◽  
Blunt Trailing Edge ◽  
Elliptic Section ◽  
Jet Blowing

SummaryExperiments performed on a low-speed circulation-controlled aerofoil are described. The aerofoil was of elliptic section with the circulation controlled by means of a jet blowing around the blunt trailing edge. Results for the lift, drag and pitching moment on the aerofoil are presented as functions of the blowing momentum coefficient and the angle of incidence. The results are for a two-dimensional aerofoil. Possible applications of this type of aerofoil are briefly discussed.

Secondary instabilities in the wake of an elongated two-dimensional body with a blunt trailing edge

2018 ◽  
Vol 846 ◽  
pp. 578-604 ◽  
Author(s):  
B. Gibeau ◽  
C. R. Koch ◽  
S. Ghaemi
Keyword(s):  
Boundary Layer ◽  
High Speed ◽  
Energy Content ◽  
Streamwise Vortex ◽  
Secondary Instability ◽  
Two Dimensional ◽  
Cylinder Wake ◽  
Trailing Edge ◽  
Piv Measurements ◽  
Blunt Trailing Edge

The secondary instability in the wake of a two-dimensional blunt body with a chord to thickness ratio of 46.5 was experimentally investigated for Reynolds numbers of 3500, 5200 and 7000 based on the blunt trailing edge height $h$. Planar, stereoscopic and high-speed particle image velocimetry (PIV) measurements were performed to characterise the wake and upstream boundary layer. The same mode B secondary instability that is found in the cylinder wake was found to be present in the wake of the elongated body studied here. The most probable wavelength of the secondary instability, defined as the spanwise distance between adjacent streamwise vortex pairs in the wake, was found to range from $0.7h$ to $0.8h$ by applying a spatial autocorrelation to the spanwise–wall-normal instantaneous fields of the $Q$-criterion. The temporal evolution of the secondary wake vortices was investigated using time-resolved stereoscopic PIV measurements and it was shown that the vortices maintain both their directions of rotation and spanwise positions during the primary vortex shedding cycles. In agreement with previous literature, the secondary instability did not greatly change as the upstream boundary layer transitioned from laminar to turbulent. Moreover, any upstream boundary layer structures were found to rapidly evolve into wake structures just past the blunt trailing edge. The wavelength of the secondary instability was shown to match the spanwise distance between adjacent low-speed zones of streamwise velocity in the wake. These undulating velocity patterns proved to be a viable method for determining the secondary instability wavelength; however, this type of analysis is highly sensitive to the energy content used for data reconstruction when proper orthogonal decomposition is applied beforehand.

Comparison of Calculated and Recorded Electron Energy-Loss Spectra of Aluminium and Carbon

1990 ◽  
Vol 48 (2) ◽  
pp. 64-65
Author(s):  
L. Reimer ◽  
R. Oelgeklaus
Keyword(s):  
Fourier Transform ◽  
Energy Loss ◽  
Electron Energy ◽  
Rotational Symmetry ◽  
Mean Free Path ◽  
Single Scattering ◽  
Specimen Thickness ◽  
Two Dimensional ◽  
Image Position ◽  
Electron Energy Loss

Quantitative electron energy-loss spectroscopy (EELS) needs a correction for the limited collection aperture α and a deconvolution of recorded spectra for eliminating the influence of multiple inelastic scattering. Reversely, it is of interest to calculate the influence of multiple scattering on EELS. The distribution f(w,θ,z) of scattered electrons as a function of energy loss w, scattering angle θ and reduced specimen thickness z=t/Λ (Λ=total mean-free-path) can either be recorded by angular-resolved EELS or calculated by a convolution of a normalized single-scattering function ϕ(w,θ). For rotational symmetry in angle (amorphous or polycrystalline specimens) this can be realised by the following sequence of operations :(1)where the two-dimensional distribution in angle is reduced to a one-dimensional function by a projection P, T is a two-dimensional Fourier transform in angle θ and energy loss w and the exponent -1 indicates a deprojection and inverse Fourier transform, respectively.

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