cases:case035

Low Reynolds Number Turbulent Flow Near Wakes


Measurements have been made in two low-Reynolds number wakes, one symmetrical and one asymmetrical with a boundary layer thickness ratio of 1.9.

The wake are formed behind a flat plate, 300 mm long, with a trailing edge thickness of 0.96 mm (approximately 0.1 times the boundary layer thickness near the trailing edge). As shown in figure 1, for the symmetric case the boundary layers were tripped symmetrically on the upper and lower surfaces of the plate, whereas for the asymmetric case the trip sizes and locations were different on the two surfaces.

 Flow configuration Fig. 1: | Flow configuration

The geometry and flow conditions were matched as closely as possible to a large eddy simulation study using a rectangular variable density mesh. If the smallest mesh size is to remain an acceptable multiple of the smallest scales the computation time will increase with Reynolds number roughly as (\(U_e\theta/\nu)^3\), where \(\theta\) is the momentum thickness and \(U_e\) the free-stream velocity. It was decided that \((U_e\theta/\nu)\) should not exceed about 600. Given that turbulence is only naturally sustainable for Reynolds numbers greater than about 300 this Reynolds number range imposed severe constraints on the experiments, in particular the tripping of the boundary layer so as to be free of residual trip effects.

The trailing edge thickness, \(t\), was about 0.1 of the boundary layer thickness, \(\delta\), at the trailing edge. This is larger than typical of an aircraft wing but comparable to that of a wing element or blade.

The wake was developed from the trailing edge of a flat plate, 300mm long, 600mm span and 0.96mm thick, the largeness of the span permitting the measurements to extend in to the far wake sufficiently free from end-flow effects. The plate length and free-stream velocity is a compromise; at 10m/s the boundary-layer thickness is about 9mm, for \(U_e\theta/\nu = 600\). Decreasing the free-stream velocity (inversely) increases the boundary layer thickness, thereby reducing probe resolution volume and position errors, but requires probe calibration over a lower velocity range and measurement of still smaller (inversely squared) wall shear stress. The free-stream velocity was 9.6m/s, and the pressure gradient was negligible. The boundary layer was tripped by means of a round wire finely glued to the plate surface. Its size was found to be crucial in terms of providing the correct amount of stimulation and, contrary to the suggestions in the literature, strongly dependent on the upstream laminar boundary layer thickness when this was relatively thick.

Hot-wire measurements were made by means of single-wire and sub-miniature x-wire probes. No wire-length effects were observed for single-wire measurements for lengths less than 1.0mm. The sensors of the cross-wire probes were nominally 0.45mm long separated by about 0.5mm.

Measurement Errors

Probe resolution errors were shown to have been small, even in the regions of the large stress gradients immediately downstream of the trailing edge. Wall shear stress was measured using Preston tubes, and by fitting the velocity profile to the logarithmic law. It is now well demonstrated (e.g. Erm and Joubert, 1991) that the logarithmic law is not Reynolds number dependent at low Reynolds numbers. The Preston tube technique requires the existence of an inner-layer law, and the calibration is implied by this law; self consistency from tubes of differing diameters and with that inferred from the velocity profile therefore implies the existence of the inner-layer form. Agreement in friction velocity \(u_{\tau}\) was within +/-1.6%.

Data available includes:

  • Development of wake widths, and integral parameters along the flow direction
  • Profiles of mean velocity, Reynolds stresses, and some higher order moments at selected streamwise locations
  • Development of mean velocity, Reynolds stresses and some higher order moments along the centreline
  • Budgets of \(k\) and \(\overline{uv}\) at selected locations for the symmetric wake case
  • Spectra of \(u'\) at selected locations for both cases.

Sample plots of selected quantities are available.

The data can be downloaded as compressed archives from the links below, or as individual files.

Symmetric Wake Asymmetric Wake
Overview/summary of data files symread-me.txt asymread-me.txt
Wake thicknesses and integral parameters sips.dat aips.dat
Profiles across the wake (Mean velocity, Reynolds stresses, triple/fourth order moments - not all available at every location)
\(x=301\) mm s301.dat a301.dat
\(x=302\) mm s302.dat a302.dat
\(x=303\) mm s303.dat
\(x=304\) mm s304.dat a304.dat
\(x=305\) mm s305.dat a305.dat
\(x=306\) mm s306.dat
\(x=308\) mm s308.dat
\(x=310\) mm s310.dat a310.dat
\(x=315\) mm s315.dat
\(x=320\) mm s320.dat a320.dat
\(x=340\) mm s340.dat a340.dat
\(x=380\) mm a380.dat
\(x=400\) mm s400.dat
\(x=460\) mm s460.dat a460.dat
\(x=520\) mm s520.dat
\(x=580\) mm s580.dat a580.dat
\(x=1000\) mm s1000.dat a1000.dat
\(x=1240\) mm a1240.dat
\(x=1960\) mm s1960.dat a1960.dat
Profiles along the geometric centreline
Mean velocity, some 2nd/3rd/4th order moments scl.dat acl.dat
\(\partial U/\partial x\), maximum \(\partial U/\partial y\) sstrain.dat astrain.dat
Profiles of mean \(V\) velocity across the wake (symmetric wake Only)
\(x=304\), \(305\), \(306\), \(308\), \(310\), \(312\), \(315\), \(320\), \(330\), \(340\) mm symvs1.dat
\(x=520\), \(580\), \(680\) mm symvs2.dat
\(x=760\), \(880\), \(1000\), \(1240\) mm symvs3.dat
Profiles along domain outer edge (symmetric wake only)
Static pressure sstatp.dat
Streamlines (symmetric wake only)
\((x,y)\) coordinates of streamlines for selected streamfunction \(\psi\) values sstream.dat
Budgets (symmetric wake only)
Readme file balread-me.txt
\(k\) budget on centreline skecl.dat
\(k\) budget at \(x=305\) mm ske305.dat
\(k\) budget at \(x=340\) mm ske340.dat
\(k\) budget at \(x=580\) mm ske580.dat
\(k\) budget at \(x=1000\) mm ske1000.dat
\(\overline{uv}\) budget at \(x=305\) mm suv305.dat
\(\overline{uv}\) budget at \(x=340\) mm suv340.dat
\(\overline{uv}\) budget at \(x=580\) mm suv580.dat
\(\overline{uv}\) budget at \(x=1000\) mm suv1000.dat
Spectra of \(u'\) - Symmetric Wake
Readme file sspec-read-me.txt
\(x=305\) mm \(x=310\) mm \(x=340\) mm
\(y=0.0\) mm 1sp305.dat 1sp310.dat 1sp340.dat
\(y=0.13\) mm 2sp305.dat 2sp310.dat 2sp340.dat
\(y=0.27\) mm 3sp305.dat 3sp310.dat 3sp340.dat
\(y=0.4\) mm 4sp305.dat 4sp310.dat 4sp340.dat
\(y=0.53\) mm 5sp310.dat 5sp340.dat
\(y=0.68\) mm 5sp305.dat 6sp310.dat 6sp340.dat
\(y=0.8\) mm 6sp305.dat 7sp310.dat 7sp340.dat
\(y=0.95\) mm 7sp305.dat 8sp310.dat 8sp340.dat
\(y=1.08\) mm 8sp305.dat 9sp310.dat 9sp340.dat
\(y=1.62\) mm 9sp305.dat 10sp310.dat
\(y=2.17\) mm 10sp305.dat 11sp310.dat
\(y=2.72\) mm 11sp305.dat 12sp310.dat
\(y=2.95\) mm 12sp305.dat 13sp310.dat 10sp340.dat
\(y=4.0\) mm 13sp305.dat
\(y=5.0\) mm 14sp310.dat
\(y=6.0\) mm 14sp305.dat
\(y=7.6\) mm 15sp305.dat 15sp310.dat 11sp340.dat
\(y=11.6\) mm 16sp305.dat 16sp310.dat 12sp340.dat
\(y=-0.0\) mm 17sp305.dat 17sp310.dat 13sp340.dat
\(y=-0.13\) mm 18sp305.dat
\(y=-0.42\) mm 19sp305.dat
\(y=-0.9\) mm 20sp305.dat 18sp310.dat 14sp340.dat
\(y=-2.9\) mm 21sp305.dat 19sp310.dat 15sp340.dat
\(y=-7.6\) mm 22sp305.dat 20sp310.dat 16sp340.dat
\(y=-11.6\) mm 23sp305.dat 21sp310.dat 17sp340.dat
Spectra of \(u'\) - Asymmetric Wake
Readme file aspec-read-me.txt
\(x=305\) mm \(x=310\) mm \(x=340\) mm
\(y=0.0\) mm 1asp305.dat 1asp310.dat 1asp340.dat
\(y=0.48\) mm 2asp305.dat 2asp310.dat 2asp340.dat
\(y=1.0\) mm 3asp305.dat 3asp310.dat 3asp340.dat
\(y=2.98\) mm 4asp305.dat 4asp310.dat 4asp340.dat
\(y=6.98\) mm 5asp305.dat 5asp310.dat 5asp340.dat
\(y=-0.0\) mm 6asp305.dat 6asp310.dat 6asp340.dat
\(y=-0.5\) mm 7asp305.dat 7asp310.dat 7asp340.dat
\(y=-1.0\) mm 8asp305.dat 8asp310.dat 8asp340.dat
\(y=-3.0\) mm 9asp305.dat 9asp310.dat 9asp340.dat
\(y=-7.0\) mm 10asp305.dat 10asp310.dat 10asp340.dat
  1. Erm, L.P., Joubert P.N. (1991). Low-Reynolds-number turbulent boundary layers. J. Fluid Mech., Vol. 230, pp. 1-44.
  2. Gough, T.D. (1996). Low Reynolds number turbulent boundary layers and wakes. PhD. Thesis, Dept. of Mechanical Engineering, University of Surrey.
  3. Gough, T.D., Hancock, P.E. (1996). Low Reynolds Number Turbulent Near Wakes. Advances in Turbulence VI. Fluid Mechanics and its Applications, Vol 36. (Eds. Gavrilakis S., Machiels L., Monkewitz P.A.), Springer.
  4. Hayakawa. M., Iida. S. (1992). Behavior of turbulence in the near wake of a thin flat plate at low Reynolds numbers, Phys. Fluids A, 4.2282-2291.

Indexed data:

case035 (dbcase, free_flow)
case035
titleLow Reynolds Number Turbulent Flow Near Wakes
authorGough, Hancock
year1986
typeEXP
flow_tag2d, axisymmetric, wake