activity
20182022
most citedDecomposition of the mean friction drag on a NACA4412 airfoil under uniform blowing/suction

30 citations · 39 across the 6 of their papers we have counts for

collaborators

6 papers

physics.flu-dyn2022★ 1 cited

High-resolution large-eddy simulations of simplified urban flows

Marco Atzori, Pablo Torres, Alvaro Vidal +3

High-fidelity large-eddy simulations of the flow around two rectangular obstacles are carried out at a Reynolds number of 10,000 based on the free-stream velocity and the obstacle…

physics.flu-dyn2021

Tripping and laminar--turbulent transition: Implementation in RANS--EVM

N. Tabatabaei, G. Fahland, A. Stroh +5

Fundamental fluid--mechanics studies and many engineering developments are based on tripped cases. Therefore, it is essential for CFD simulations to replicate the same forced trans…

physics.flu-dyn2021★ 30 cited

Decomposition of the mean friction drag on a NACA4412 airfoil under uniform blowing/suction

Yitong Fan, Marco Atzori, Ricardo Vinuesa +3

The application of drag-control strategies on canonical wall-bounded turbulence, such as periodic channel and zero- or adverse-pressure-gradient boundary layers, raises the questio…

physics.flu-dyn2019

Coherent structures and secondary flow in turbulent square duct

Marco Atzori, Ricardo Vinuesa, Adrián Lozano-Durán +1

The aim of the present work is to investigate the role of coherent structures in the generation of the secondary flow in a turbulent square duct. The coherent structures are define…

physics.flu-dyn2018★ 8 cited

Assessment of skin-friction-reduction techniques on a turbulent wing section

M. Atzori, R. Vinuesa, A. Stroh +2

The scope of the present project is to quantify the effects of uniform blowing and body-force damping on turbulent boundary layers subjected to a non-uniform adverse-pressure-gradi…

physics.flu-dyn2018

Reynolds-number effects in turbulent boundary layers around wing sections

Ricardo Vinuesa, Prabal Negi, Marco Atzori +3

Four well-resolved LESs of the turbulent boundary layers around a NACA4412 wing section, with Rec ranging from 100,000 to 1,000,000, were performed at 5 degree angle of attack. By…