Fishes have an enormous diversity of body shapes and
fin morphologies. From a hydrodynamic standpoint, the
functional significance of this diversity is poorly
understood, largely because the three-dimensional flow
around swimming fish is almost completely unknown.
Fully three-dimensional volumetric flow measurements
are not currently feasible, but measurements in multiple
transverse planes along the body can illuminate many of
the important flow features. In this study, I analyze flow in
the transverse plane at a range of positions around bluegill
sunfish Lepomis macrochirus, from the trailing edges of
the dorsal and anal fins to the near wake. Simultaneous
particle image velocimetry (PIV) and kinematic measurements
were performed during swimming at 1.2·body·lengths·s–1
to describe the streamwise vortex structure, to quantify
the contributions of each fin to the vortex wake, and to
assess the importance of three-dimensional flow effects in
swimming.
In this study we present scaled 2D physical models based on extensional deformation of a cohesive mixture of sand and gypsum. We studied the detailed evolution of normal faults in a graben above a rigid basement, in order to evaluate its deformation in time and space over a wide scale range. The material properties and the apparatus setup allow a scaling of the laboratory experiments with respect to the natural prototypes in the North German Basin. The structural evolution and displacement field was analysed by digital photography and Particle Image Velocimetry (PIV).
Flow and far-field noise measurements are taken on a conical Convergent-
Divergent nozzle similar to the nozzles employed on high-performance
tactical jets. Matching flow and far-field computations are presented,
produced by Large Eddy Simulation and the Kirchhoff integral method.
The conditions examined are those in which the nozzle is operated at its
design Mach number of 1.56 while forward flight is simulated at Mach
numbers of 0.1, 0.3 and 0.8. Both measurement and LES show that
increasing forward flight Mach number to the high subsonic range
shortens the initial shock cell size, and weakens the shock cells induced by
the nozzle throat relative to the shock cells induced by the nozzle lip. LES
shows that high forward flight speed substantially reduces the noise
radiated into the forward quadrant where shock noise is dominant. It also
removes the screech tone entirely.
Flow and far-field noise measurements are taken on a conical Convergent-
Divergent nozzle similar to the nozzles employed on high-performance
tactical jets. Matching flow and far-field computations are presented,
produced by Large Eddy Simulation and the Kirchhoff integral method.
The conditions examined are those in which the nozzle is operated at its
design Mach number of 1.56 while forward flight is simulated at Mach
numbers of 0.1, 0.3 and 0.8. Both measurement and LES show that
increasing forward flight Mach number to the high subsonic range
shortens the initial shock cell size, and weakens the shock cells induced by
the nozzle throat relative to the shock cells induced by the nozzle lip. LES
shows that high forward flight speed substantially reduces the noise
radiated into the forward quadrant where shock noise is dominant. It also
removes the screech tone entirely.
Increasingly smaller electronics requires improvement in performance of cooling systems to keep it operating
reliably. We present herein a novel experimental study of convective heat transfer in serpentine
microchannels with segmented liquid–liquid emulsions. It is demonstrated that this concept yields significant
Nusselt number enhancement in microchannel heat sinks compared to that obtained using single
phase liquid cooling. Laser Induced Fluorescence (LIF) is employed to measure temperature of the coolant
with and without droplets, and micro-PIV is used to determine velocity field. For the segmented flow, up
to four-fold increase of the Nusselt number was observed compared to pure water flow.
The idea of manipulating flow to change its characteristics is over a century old. Manipulating instabilities of a jet to increase its mixing and to reduce its radiated noise started in the 1970s. While the effort has been successful in low-speed and low Reynolds number jets, available actuators’ capabilities in terms of their amplitude, bandwidth, and phasing have fallen short in control of high-speed and high Reynolds number jets of practical interest. Localized arc filament plasma actuators have recently been
developed and extensively used at Gas Dynamics and Turbulence Laboratory (GDTL) for control of highspeed and high Reynolds number jets. While the technique has been quite successful and is very
promising, all the work up to this point had been carried out using small high subsonic and low supersonic jets from a 2.54 cm diameter nozzle exit with a Reynolds number of about a million. The
preliminary work reported in this paper is a first attempt to evaluate the scalability of the technique.
Grease is commonly used to lubricate various machine components such as rolling element
bearings, open gears etc. Better understanding of the flow properties of grease will contribute to
understanding the lubrication mechanism in bearings and flow in lubrication systems. In an earlier paper
Micro Particle Image Velocimetry (μPIV) techniques were used to study the flow in a rectangular channel.
The present paper is an extension of this work where restrictions were applied in such a channel, which
creates a much more complex velocity field. The grease is seeded with fluorescent particles, which are
illuminated by a double-pulsed laser. The test geometries that are used in this study are a channel with one
flat restriction and one with two flow restrictions in a similar channel. The stationary grease mass-flow and
the two dimensional velocity fields have been monitored for different pressure drops. For the channel with
one flat restriction, the flow was measured to be symmetric at the inlet and outlet, and the distance for the
flow to fully develop is comparable with the height of the channel; Slow motion was followed near the step
corner at the inlet. For the channel with two flow restrictions, the vector profiles show that the maximum
velocity appears at the restrictions; In-between the two restrictions, a part of the grease is not moving. This
particularly applies to cases with low-pressure drop and where high consistency grease was used.