READ ME File For 'Dataset for Mitigation of transonic shock buffet on a supercritical aerofoil through wavy leading edges'

Dataset DOI: https://doi.org/10.5258/SOTON/D1719

ReadMe Author: Degregori Enrico, University of Southampton

This dataset supports the publication:
AUTHORS: E. Degregori, J.W. Kim
TITLE:Mitigation of transonic shock buffet on a supercritical aerofoil through wavy
leading edges
JOURNAL: Physics of Fluids

The figures are as follows:

./Figure1/ Computational domain highlighting physical domain and sponge layer (a), close up near the aerofoil and the wake with 25% of points shown and the streamwise velocity flow field (b), close up near the aerofoil with 25% of points shown (c) and mesh over the surface of the wavy aerofoil (repeated 5 times) with 50% of the points shown (d).

./Figure2/ -> Grid validation for SLE aerofoil. Comparison of mean aerodynamic characteristics, mean pressure coefficient distribution (a) and mean skin friction coefficient distribution (b). Comparison of unsteady aerodynamic characteristics, lift coefficient time signal (c) and lift coefficient PSD with respect to the Strouhal number (d).

./Figure3/ -> Mean pressure coefficient distribution at WLE peak, hill and trough and over SLE at α = 7.0 for WLE1 (a), WLE2 (b) and WLE3 (c) aerofoils.

./Figure4/ -> Mean skin friction coefficient distribution over the suction side at WLE peak, hill and trough and over SLE at α = 7.0 for WLE1 (a), WLE2 (b) and WLE3 (c) aerofoils.

./Figure5/ -> Relative change in aerodynamic forces between SLE and WLE cases in terms of piecewise distribution of lift along the chord calculated from wall pressure (d(∆C L )/dx) for WLE1 (a), WLE2 (b) and WLE3 (c) aerofoils. The relative difference between SLE and WLE cases are denoted by ∆{.} = {.} W LE − {.} SLE.

./Figure6/ -> Relative change in aerodynamic forces between SLE and WLE cases in terms of piecewise distribution of pressure drag along the chord calculated from wall pressure (d(∆C D )/dx) for WLE1 (a), WLE2 (b) and WLE3 (c) aerofoils. The relative difference between SLE and WLE cases are denoted by ∆{.} = {.} W LE − {.} SLE.

./Figure7/ -> Mean lift (a), drag (b), and efficiency (c) spanwise distribution over WLE1, WLE2 and WLE3 aerofoils at α = 7.0.

./Figure8/ -> Comparison of LE flow field at WLE1 trough (a,c) and over SLE (b,d). Mach number contour highlighting the sonic line (black line) (a,b). Pressure contour highlighting the LSB canopy (red line) and the streamlines close to the wall (c,d). Mean pressure coefficient distribution in the LE region at WLE1 peak, hill and trough and over SLE (e).

./Figure9/ -> Lift (a) and drag (b) coefficient time signal for SLE aerofoil and WLE1, WLE2 and WLE3 aerofoils.

./Figure10/ -> Lift (a) and drag (b) coefficient power spectral density with respect to the Strouhal number for SLE aerofoil and WLE1, WLE2 and WLE3 aerofoils.

./Figure11/ -> Pressure gradient magnitude flow field around SLE aerofoil during one cycle of the shock buffet oscillation: most upstream position (a), shock wave downstream movement (b), most downstream position (c) and shock wave upstream movement (d).

./Figure12/ -> Power spectral density with respect to the Strouhal number (a) and time signal (b) of wall pressure at different chordwise locations over the upper surface of SLE aerofoil.

./Figure13/ -> Pressure gradient magnitude flow field at the hill section of WLE3 aerofoil during one cycle of the shock buffet oscillation: most upstream position (a), shock wave downstream movement (b), most downstream position (c) and shock wave upstream movement (d).

./Figure14/ -> Power spectral density with respect to the Strouhal number (a) and time signal (b) of wall pressure at different chordwise locations over the upper surface of WLE2 trough section.

./Figure15/ -> Pressure gradient magnitude flow field at the hill section of WLE2 aerofoil at the high frequency oscillation’s minimum (a) and maximum (b).

./Figure16/ -> Instantaneous original (a) and filtered (b) spanwise vorticity at the trough section of WLE2 aerofoil.

./Figure17/ -> Filtered pressure coefficient field around the trailing edge of SLE aerofoil during one cycle of the high frequency oscillation. Negative filtered pressure coefficient shows the release of a vortex from the trailing edge (a), followed by a region of positive filtered pressure coefficient (b), then the cycle starts again and another vortex is released (c).

./Figure18/ -> Filtered spanwise vorticity field at the trough section of WLE2 aerofoil during one cycle of the high frequency oscillation. The minimum (a), maximum (b) and the following minimum (c) of the oscillation are shown.

./Figure19/ -> Streamwise velocity field at the trough section of WLE2 aerofoil showing the minimum (a) and maximum (b) of the LSB breathing oscillation, related to periodic thickening and thinning of the LSB respectively. Black line highlights LSB canopy.

Date of data collection: 12, 2020

Licence: CC BY

Date that the file was created: 01, 2021