Two types of shear flows are investigated in this thesis; numerical simulations are performed for the analysis and control of the perturbation arising in a boundary layer over a flat plate, whereas PIV measurements are analysed for the investigation of a confined turbulent jet. Modal structures of the flows are identified: the aim is to understand the flow phenomena and to identify reduced-order models for the feedback control design. The attenuation of three-dimensional wavepackets of streaks and Tollmien-Schlichting (TS) waves in the boundary layer is obtained using feedback control based on arrays of spatially localized sensors and actuators distributed near the rigid wall. In order to tackle the difficulties arising due to the dimension of the discretized Navier-Stokes operator, a reduced-order model is identified, preserving the dynamics between the inputs and the outputs; to this end, approximate balanced truncation is used. Thus, control theory tools can be easily handled using the low-order model. We demonstrate that the energy growth of both TS wavepackets and streak-packets is substantially and efficiently mitigated, using relatively few sensors and actuators. The robustness of the controller is investigated by varying the number of actuators and ensors, the Reynolds number and the pressure gradient. The configuration can be possibly reproduced in experiments, due to the localization of sensing and actuation devices. A complete analysis of a confined turbulent jet is carried out using timeresolved PIV measurements. Proper orthogonal decomposition (POD) modes and Koopman modes are computed and analysed for understanding the main features of the flow. The frequencies related to the dominating mechanisms are identified; the most energetic structures show temporal periodicity. / QC 20110214

In the context of building a framework for active flow control of turbulent boundary layers in wings, a set of large-eddy simulation (LES) are implemented in OpenFOAM. The flow around a NACA4412 wing profile is simulated at 5° angle of attack and Re_c = 400˙000. Validation of the uncontrolled flow results is performed with respect to the dataset generated by Vinuesa et al. (2018) at the same aerodynamic configuration. Afterwards, two different flow control strategies are analyzed over the suction side (SS) of the wing to yield skin friction drag reduction and an overall improvement of the aerodynamic efficiency. The region subject to the actuation spans 0.25 x_ss/c to 0.:86 x_ss/c, where c is the chord length of the wing. In the current setup, uniform blowing (BLW) and suction (SCT) control schemes show close agreement with the trends presented by Atzori (2021). Indeed, BLW decreases the viscous drag, but increases its pressure contribution and penalizes the lift, thus lowering the global efficiency of the wing, while SCT has an opposite effect. Thus, these methods behave similarly to pressure gradients (PGs) conditions, as BLW enhances the APG, whereas SCT damps it. The streamwise travelling waves strategy is then assessed for three set-ups characterized by different phase speeds. A consistent skin friction drag reduction and efficiency improvement are observed for two cases, while milder benefits are recorded even when drag increase was expected. Trends which have already been reported in the literature by Quadrio et al. (2009) and Skote (2014) are identified, i.e. the effects of this actuation to be mainly enclosed in the viscous sub-layer and the gross amount of drag reduction to be dependent on the wave relative speed; however, it is believed that the PGs conditions over the SS of the wing significantly alters the outcomes of the chosen parameters. Eventually, Reynolds averaged Navier-Stokes (RANS) simulations are performed to assess their accuracy with respect to the generated LES set-up, in the effort to enable a multi-fidelity approach for future works.

No description available.

No description available.

No description available.

No description available.

No description available.

No description available.

No description available.

No description available.