------------------------------------------------------------------------------------------ Wingtip Vortex Structure in the Near Field of Swept-Tapered Wings; Physcis of Fluids; 2020 ------------------------------------------------------------------------------------------ This data has been made open source to accompany the above manuscript by Dr. Shaun Skinner (skinner1@umd.edu), Dr. Richard Green (richard.green@glasgow.ac.uk), and Dr. Hossein Zare-Betash (hossein.zare-behtash@glasgow.ac.uk). This data was collected at the Univerity of Glasgow in the de Havilland National Wind Tunnel Facility during Dr. Skinner's Doctoral research (The dissertation for this doctoral research can be found here: https://eleanor.lib.gla.ac.uk/record=b3326605). The authors would like to express our gratitude and appreciation to the National Wind Tunnel Facility (EPSRC Grant number: EP/L024888/1) at the University of Glasgow. Acknowledgment also goes to Zephyr Business Services (Grant number: 74603) and the Royal Aeronautical Society Centennial Scholarship (Grant number:21-657/A-SKI) for funding this work. The purpose of making this data open source is primarily to offer high spatial resolution data (1mm) to the wider CFD community in the hope that it will provide useful for numerical validation and aid in cultivating a deeper understanding of vortex dynamics. Data for angles of attack (0 to 12 degrees) for five downstream planes in the near-field are provided for the planar wing arrangemet. All stereoscopic particle imaging velocimetry (sPIV) data provided here has been time averaged over 1800 frames at 200Hz. Vortex meander has been corrected for using a helicity-based spatial localisation filter. The data provided has not been non-dimensionalised; Velocity: m/s, spatial coordinates: mm. ------------------------------------------------------------------------------------------ Experimental parameters ------------------------------------------------------------------------------------------ Reynolds Number: 1.5 million (based on the wing's *MAC) Mach Number: 0.145 Freestream velocity: *~50 m/s Dynamic pressure: ~1531.25 Pa Density: ~1.225 kg/m^3 Wing parameters Aerofoil Section: NACA 63-412 Surface Finish: Roughness grade N3 MAC: 0.44 m Root Chord: 0.7 m Wing Area: 0.5717 m^2 Taper Ratio: 0.21 Aspect ratio: 4.12 Quarter Chord Sweep: 30 degrees Wing Twist: 0 degrees * MAC- Mean Aerodynamic Chord * Drifts in freestream velocty occured as a function of the freestream air temperature (density); at temperature increased, so did the freestream velocity. This was done to maintain the Reynolds number. * Please refer to the manuscripts below for information regarding to: the sPIV setup; sPIV error analysis; vortex meander corrections; model design; and additional information regarding the wind tunnel (e.g. longitudinal, pressure gradients, boundary-layer growth rates, drag corrections) or the wing section (e.g. wing separation, and wing structural dynamics). ========================================================================================== ------------------------------------------------------------------------------------------ Information about the sPIV datasets ------------------------------------------------------------------------------------------ * Spatial resolution for all calibrations is ~1mm. * Only averaged data is provided. Please contact corresponding author if more detailed data would be for you purposes. *Ux - Axial velocity [m/s] *Uy & Uz - In-plane velocities [m/s] * Import data as a numeric Matrix To plot (in Matlab): figure() surf(X_Coord,Y_Coord,(Velocity component),'EdgeColor','none') view(2) % Create colorbar colorbar set(gcf,'renderer','zbuffer') hcb=colorbar('fontsize',10); shading interp % Axes axis image xhandle=xlabel('y [mm]','fontsize',10,'interpreter','latex'); yhandle=ylabel ('z [mm]','fontsize',10,'interpreter','latex'); * Note: At planes close to the wing, the wing tip is visible in the PIV Image. ========================================================================================== ----------------------- Simple data manipulations ----------------------- Velocity Magnitude: Vmag = ((Ux.^2)+(Uy.^2)+(Ux.^2)).^(1/2); In-plane Velocity: inplane_velocity = ((Uy.^2)+(Uz.^2)).^(1/2); Inplane Vorticity [Vort,av] = curl((X_Coord,Y_Coord,Uy,Uz); * Note: This method of vorticity calcultion is not used for the data presented in the manuscipt. ========================================================================================== ------------------------------------------------------------------------------------------ Related manuscripts ------------------------------------------------------------------------------------------ S.N. Skinner and H. Zare-Behtash. Study of a C-wing Configuration for Passive Drag and Load Alleviation. Journal of Fluids and Structures, 78:175-196, 2018. S.N. Skinner and H. Zare-Behtash. State-of-the-art in aerodynamic shape optimisation methods. Applied Soft Computing, 62:933-962, 2018. S.N. Skinner and H. Zare-Behtash. Semi-Span Wind Tunnel Testing Without Conventional Peniche. Experiments in Fluids, 58(163), 2017. M. Giuni and R.B. Green. Vortex Formation on Squared and Rounded Tip. Aerospace Science and Technology, 29(1):191-199, 2013. ==========================================================================================