most citedUnsteady aerodynamic effects in small-amplitude pitch oscillations of an airfoil

56 citations · 66 across the 2 of their papers we have counts for

collaborators

7 papers

physics.flu-dyn2019

Global stability of rigid-body-motion fluid-structure-interaction problems

Prabal S. Negi, Ardeshir Hanifi, Dan S. Henningson

A rigorous derivation and validation for linear fluid-structure-interaction (FSI) equations for a rigid-body-motion problem is performed in an Eulerian framework. We show that the…

physics.flu-dyn201956 cited

Unsteady aerodynamic effects in small-amplitude pitch oscillations of an airfoil

Prabal S. Negi, Ricardo Vinuesa, Ardeshir Hanifi +2

High-fidelity wall-resolved large-eddy simulations (LES) are utilized to investigate the flow-physics of small-amplitude pitch oscillations of an airfoil at Re = 100,000. The inves…

physics.flu-dyn201910 cited

Turbulent boundary layers around wing sections up to Rec = 1,000,000

R. Vinuesa, P. S. Negi, M. Atzori +3

Reynolds-number effects in the adverse-pressure-gradient (APG) turbulent boundary layer (TBL) developing on the suction side of a NACA4412 wing section are assessed in the present…

physics.flu-dyn2019

A realizable data-driven approach to delay bypass transition with control theory

Pierluigi Morra, Kenzo Sasaki, Ardeshir Hanifi +2

The current work presents a realizable method to control streaky disturbances in boundary layer flows and delay transition to turbulence via active flow control. Numerical simulati…

physics.flu-dyn2019

On the role of actuation for the control of streaky structures in boundary layers

Kenzo Sasaki, Pierluigi Morra, André V G. Cavalieri +2

This work deals with the closed-loop control of streaky structures induced by free-stream turbulence in a zero-pressure gradient, transitional boundary layer, by means of localized…

physics.flu-dyn2018

Assessment of turbulent boundary layers on a NACA4412 wing section at moderate Re

R. Vinuesa, S. M. Hosseini, A. Hanifi +2

The results of a DNS of the flow around a wing section represented by a NACA4412 profile, with Rec = 400, 000 and 5 degree angle of attack, are presented in this study. The high-or…