The Role of Spanwise Flow for Swept Wing Separation Control with Varied Spanwise Jet Spacing

Walker, Michael M.; Hipp, Kyle D.; Bons, Jeffrey P.

doi:10.2514/6.2016-3120

Cited by 3 publications

(1 citation statement)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In addition, these complex flow structures over moderately swept wings are still a challenge for computer simulations (7)(8)(9)(10)(11)(12)(13)(14) . For example, Li and Leschziner (7,8) used the large eddy simulation (LES) and a wall function approach to simulate the highly complex separated flow over a swept wing.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the flow structures over a 40° swept wing

Zhang

Jaworski²,

McParlin

et al. 2019

Aeronaut. j.

View full text Add to dashboard Cite

Flow over a moderately swept wing is characterised by complex localised flow vortex topologies such as ‘closed’ separation bubbles or ‘open’ separation structures. A model of a complex cambered, twisted, tapered wing with 40° leading edge sweep, representative of those designed for manoeuvre at high subsonic Mach numbers, was investigated using the oil-film visualisation, stereo particle image velocimetry and force moment measurements. Wind-tunnel tests were conducted at a range of Reynolds number from 2.1×105 to 8.4×105 and at angles of incidence from −1° to 22°. Still images combined with video clips enable flow patterns over the wing model to be interpreted more clearly and accurately. Using successive images extracted from the video of flow visualisation, the movement of the oil pigment has been estimated. The influence of the Reynolds number and incidence angle was discussed through analysing the flow pattern over the wing surface. Additionally, the link between the flow structures present and the wing aerodynamic performance was studied.

show abstract