Experiments have been conducted on a swept wing model in a low-turbulence wind tunnel
at chord Reynolds number of to investigate the unsteady interaction of a forward-facing step …

This work experimentally investigates plasma actuator (PA) forcing effects on the base flow
and developing crossflow (CF) instabilities in a swept wing boundary layer. Spanwise …

The accumulation of aerodynamic heat at the rudder shaft of a hypersonic vehicle will
reduce the vehicle's aerodynamic performance. This paper proposes a trailing-edge curved …

This work examines the control of cross-flow instabilities (CFIs) and laminar–turbulent
transition on a swept wing, through the plasma-based base flow modification (BFM) …

This work investigates the response of a transitional boundary layer to spanwise-invariant
dielectric barrier discharge plasma actuator (PA) forcing on a 45 swept wing at a chord …

In a three-dimensional boundary layer with spanwise constant flow and chordwise
acceleration, which is unique to the vicinity of the leading edge of a swept wing, an inviscid …

In this work a nanosecond-pulsed dielectric barrier discharge actuator is simulated to
investigate the plasma and surface charge behavior during the startup phases of a given …

Mechanism of hydrodynamic noise generation in a subsonic flat plate boundary layer by a
barrier discharge plasma actuator is described. The origin of the pulsations is an inscintric …

Cancellation of the cross-flow vortices in a swept-wing boundary layer is attempted by
plasma actuator array in numerical simulation. The response of the boundary layer to the …

View Video Presentation: https://doi. org/10.2514/6.2023-2389. vid This study is an
experimental investigation on the electromechanical characteristics of a particular geometry …