J. Serpieri
24 records found
1
Authored
Cross-Flow Instability
Flow diagnostics and control of swept wing boundary layers
In the present work, laminar flow control, following the discrete roughness elements (DRE) strategy, also called upstream flow deformation (UFD) was applied on a 45◦ swept-wing at a chord Reynold’s number of Rec = 2.1 · 106 undergoing cross-flo ...
Control of laminar-to-turbulent transition on a swept-wing is achieved by base-flow modification in an experimental framework, up to a chord Reynolds number of 2.5 million. This technique is based on the control strategy used in the numerical simulation by Dörr & Kloker (J ...
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 b ...
A combined experimental and numerical approach to the analysis of the secondary stability of realistic swept-wing boundary layers is presented. Global linear stability theory is applied to experimentally measured base flows. These base flows are three-dimensional laminar bound ...
In the present work, laminar flow control, following the distributed roughness elements (DRE) - upstream flow deformation (UFD) strategy, was attempted on a 45° swept wing at Re = 2:17·106undergoing cross-flow (CF) instability transition. Active roughness-like AC-DB ...
In the current study, selective forcing of cross-flow instability modes evolving on a swept wing at is achieved by means of spanwise-modulated plasma actuators, positioned near the leading edge. In the perspective of laminar flow control, the followed methodology holds on the ...
Stationary waves approximately aligned with the flow direction develop in the laminar boundary layer of swept wings in low freestream turbulence conditions. These, so-called Crossflow vortices, undergo spatial amplification and amplitude saturation and deeply modify the bounda ...
An experimental investigation of primary and secondary crossflow instability developing in the boundary layer of a 45° swept wing at a chord Reynolds number of 2.17 × 106 is presented. Linear stability theory is applied for preliminary estimation of the flow stabili ...