Measurements in the near-wake of a turbulent wing-body junction
Abstract
Turbulent wing-body junction flows arise from the interaction between a turbulent boundary layer and a surface mounted streamlined obstacle, and are frequently encountered in aerodynamic and hydrodynamic applications. This study uses two-dimensional, three component stereo PIV measurements to investigate the statistical and instantaneous properties of a wing-body near-wake at moderate Reynolds number. The measurements were acquired in an open-return boundary layer wind tunnel at the University of Melbourne. The approach zero pressure gradient boundary layer at Rθ = 10 , 000 interacts with a `Rood wing' composed of a 3:2 elliptical leading edge joined to a NACA 0020 profile, with a chord length C = 168 mm, maximum thickness T = 40 mm, and height H = 80 mm. The freestream velocity was about 20 m/s. Three component velocity measurements were collected at five different streamwise locations ranging from 0.075C to 1C downstream of the trailing edge of the airfoil, whose angle-of-attack was also varied from -15 to +15 degrees in increments of 5 degrees. Results focus on the three dimensional structure of the near-wake flow and the influence of the necklace vortices that form in front of the body and pass through the wake. Variations with angle of attack are described.
This research was support by the Office of Naval Research, Grant No. N0014-17-1-2307.- Publication:
-
APS Division of Fluid Dynamics Meeting Abstracts
- Pub Date:
- November 2019
- Bibcode:
- 2019APS..DFDG40008K