In-situ boundary layer transition detection on multi-segmental (a)synchronous morphing wings

This paper presents an experimental method to detect in-situ the location of transition on a multi-segmental trailing edge camber morphing wing during synchronous and asynchronous morphing. The wing consists of six independently morphing segments with two of the segments instrumented with eight embedded piezoelectric sensors distributed...

Piezo-sensors for in-situ boundary layer monitoring on morphing wings: Development, validation and implementation

This thesis describes the development, validation and implementation of piezoelectric flow sensors. These sensors are meant to measure flow phenomena such as transition and separation in the boundary layer of an aircraft wing. Such information can be used<br/>as input variables to a control loop to push laminar-to-turbulent transition towards...

Conditioning of unsteady cross-flow instability modes using dielectric barrier discharge plasma actuators

In this study, experiments are performed towards the identification and measurement of unsteady modes occurring in a transitional swept wing boundary layer. These modes are generated by the interaction between the primary stationary and travelling cross-flow instabilities or by secondary instability mechanisms of the stationary cross-flow...

Effect of Local DBD Plasma Actuation on Transition in a Laminar Separation Bubble

This work examines the effect of local active flow control on stability and transition in a laminar separation bubble. Experiments are performed in a wind tunnel facility on a NACA 0012 airfoil at a chord Reynolds number of 130 000 and an angle of attack of 2 degrees. Controlled disturbances are introduced upstream of a laminar separation...