Non-Modal Growth Induced by Discrete Roughness Elements in a Swept Wing Boundary Layer: Modelling and Diagnostics

Laminar-to-turbulent boundary layer transition on the wings and stabilizers of aircraft leads to a large increase in the skin-friction drag they experience during flight. This has motivated prolific research into understanding and delaying the transition process, in an effort to improve the economic and ecological impact of air travel. The swept...

Cross-Flow Instability Control through Base-Flow Modification using AC-DBD Plasma Actuators: An Experimental Investigation

Following recent proof of swept wing laminar-to-turbulent boundary layer transition delay through base-flow modification using AC-DBD plasma actuators, an experimental investigation is performed to study the responsible physical mechanism. An experiment is conducted on a 45° swept wing in the anechoic wind tunnel at the Delft University of...