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This paper describes an experiment that was carried out in the Twisted Flow Wind Tunnel at The University of Auckland to measure a detailed set of pressure distributions on a rigid 1/15th scale model of a modern asymmetric spinnaker.
The use of the 3DL process for the upwind sails led to great efficiency gains in terms of structural integrity, and the development of a twisted flow wind tunnel was invaluable in the development of the downwind sails.
The comparison between the calculated and measured sound fields shows good agreement for the maximum sound pressure levels, but differences were observed in the directivity characteristics, which are mainly caused by the different velocities in the jet and the external flow (wind tunnel flow).
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A similar counterflow ion mobility instrument incorporating a high-flow wind tunnel but operated in a nontrapping mode was also described by Agbonkonkon and Lee. Park and co-workers recently described the use of a stacked ring ion trap in a mobility-selective mode, in a technique they named trapped ion mobility spectrometry (TIMS).
Different measurement techniques were adapted to the flow and wind tunnel requirements to provide an accurate characterization of the flow developing over the splitter surface.
Fig. 3 Mono-strut effect on aircraft flow in wind tunnel.
The Mach-Zehnder interferometer's relatively large and freely accessible working space, and its flexibility in locating the fringes has made it the interferometer of choice for visualizing flow in wind tunnels, and for flow visualization studies in general.
A full-scale 2.5 MW wind turbine airfoil section, typical for the near tip, was placed in the free stream flow of the wind tunnel at the Saint Anthony Falls Laboratory, University of Minnesota.
It is tested on two different test cases with the Euler equations: flow over a wedge and Mach-3 flow in a wind tunnel with a step.
They set the flow velocity to approximately 20 m/s, and the particles were blown by this flow in the wind tunnel.
The results validated the new Launch Ascent and Vehicle Aerodynamics flow solver against wind tunnel testing.
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