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Active flow control of the turbulent boundary layer over a NACA4412 wing profile for skin friction drag reductionSemprini Cesari, Giacomo January 2023 (has links)
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.
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A computational study for the utilization of jet pulsations in gas turbine film cooling and flow controlKartuzova, Olga Valeryevna 29 June 2010 (has links)
No description available.
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Control of Hypersonic High Angle-Of-Attack Re-Entry Flow Using a Semi-Empirical Plasma Actuator ModelAtkinson, Michael D. 11 May 2012 (has links)
No description available.
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Experimental Study of Fillets to Reduce Corner Effects in an Oblique Shock-Wave/Boundary-Layer InteractionHirt, Stefanie M. 09 February 2015 (has links)
No description available.
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Physics and Control of Flow Over a Thin Airfoil using Nanosecond Pulse DBD ActuatorsGhasemi Esfahani, Ata January 2017 (has links)
No description available.
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The Effect of Multiple Scales on Fractal-Grid-Generated TurbulenceOmilion, Alexis Kathleen 11 June 2018 (has links)
No description available.
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A NUMERICAL STUDY OF THE EFFECT OF FREQUENCY OF PULSED FLOW CONTROL APPLIED TO A RECTANGULAR CAVITY IN SUPERSONIC CROSSFLOWSTANEK, MICHAEL JOSEPH 27 September 2005 (has links)
No description available.
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Large-Eddy Simulation and Active Flow Control of Low-Reynolds Number Flow through a Low-Pressure Turbine CascadePOONDRU, SHIRDISH 18 April 2008 (has links)
No description available.
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Active Separation Control of High-Re Turbulent Separated Flow over a Wall-Mounted Hump using RANS, DES, and LES Turbulence Modeling ApproachesGan, Subhadeep 03 August 2010 (has links)
No description available.
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Characterization of the jet emanating from a self-exciting flexible membrane nozzleLakhamraju, Raghava Raju 05 October 2012 (has links)
No description available.
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