Study of a C-wing configuration for passive drag and load alleviation

Abstract

Non-planar wing configurations are often hypothesised as a means for improving the aerodynamic efficiency of large transport aircraft; C-wings may have the ability to exploit and unify drag reduction, aeroelasticity, and dynamics and control but their capacity to do so is ambiguous. The purpose of this work is to provide an experimental demonstration with the aim of verifying the C-wing configurations practical application. Thus, the main objective of this investigation is to

Wingtip vortex structure in the near-field of swept-tapered wings

“…While not addressed in this study, Skinner and Zare-Behtash 55 and Skinner 57 provide information regarding the model's structural dynamics and investigate the aerodynamic performance of the wing which is not explicitly shown in this work, but is referred to. For the same range of conditions, this study aims to quantify the development of the trailing vortex system produced by the wing between 0…”

“…For the experimental conditions presented here, the turbulence intensity along the centre line of the working section length is 0.4%. Further, detailed characterisation of the dH working section is provided elsewhere 57 .…”

“…The light sheet arrangement was set up to accommodate the dominant out-of-plane tracer displacements, while providing sufficient illumination of particles to track in-plane tracer displacements over the laser separation pulse, ∆t. The laser separation pulse/experimental arrangement was selected to resolve both the tangential (in-plane) and the axial (out-ofplane) velocity components; see Skinner 57 for further information. In this work, a pulse separation of ∆t = 25µs has been used with a data acquisition rate of 200Hz.…”

“…calculated utilising an eight-point scheme presented by Raffel et al 59 . corresponds to the rotational speed of the wind tunnel fan (≈ 615 rpm) 55 . Figure 6(a)…”

“…This investigation documents the wake vortex formation, analysing the evolution of the tangential and axial velocity distribution, the vortex core shape, the vorticity distribution, and the low frequency (≤ 100Hz) turbulent properties of the vortex core. Skinner and Zare-Behtash 55 have previously assessed the aerodynamic and aeroelastic behaviours of the wing which will be referred to throughout this work.…”