Author
Valentina Motta
Other affiliations: University of Salento
Bio: Valentina Motta is an academic researcher from General Electric. The author has contributed to research in topics: Plasma actuator & Airfoil. The author has an hindex of 1, co-authored 4 publications receiving 24 citations. Previous affiliations of Valentina Motta include University of Salento.
Topics: Plasma actuator, Airfoil, Linear compressor, Trailing edge, Cascade
Papers
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TL;DR: In this article, the authors evaluated the feasibility of using multiple dielectric barrier discharge (DBD PAs) plasma actuators as a novel approach for load alleviation and stability control of airfoils in unsteady flow.
37 citations
TL;DR: In this article, the effects of dielectric barrier discharge (DBD) plasma actuators on the aeroelastic control of a subsonic compressor cascade were investigated.
10 citations
TL;DR: The data are related to the study focused on the evaluation of the effects of an active flow control system on the performance of an airfoil in an unsteady flow, with particular focus on the influence of actuation parameters on the global performances.
TL;DR: In this paper, a comparison of different plasma actuation strategies for aero-elastic control on a linear compressor cascade is presented, where both experimental and raw data of the CFD simulations are presented.
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34 citations
TL;DR: In this paper, the authors proposed a surrogate-based optimization (SBO) technique to alleviate the computational burden of aerodynamic shape optimization (ASO) to delay and mitigate the deep dynamic stall characteristics of airfoils.
33 citations
TL;DR: In this paper, a rotating gliding arc (RGA) in three different discharge powers (from 35 W to 250 W) was designed to enhance ignition and combustion in a swirl model combustor with a flow speed from 15m/s to 60 m/s.
31 citations
TL;DR: In this paper, the effects of dielectric-barrier-discharge plasma (DBD) actuator layout on the plasma-induced thermal characteristics and evaluate their effectiveness for aircraft icing mitigation.
27 citations
TL;DR: In this article, a dielectric barrier discharge (DBD) plasma actuator is used to control air flow around the NACA (National Advisory Committee for Aeronautics)0015 airfoil.
Abstract: This paper presents the results of numerical simulation of a dielectric barrier discharge (DBD) plasma actuator and shows its effectiveness to control air flow around the NACA(National Advisory Committee for Aeronautics)0015 airfoil. The actuator consists of two tape electrodes separated by a dielectric layer, and it is mounted on the suction side of the airfoil at 18% of the chord length. An alternating voltage with 20 kV magnitude and 10 kHz frequency is applied between both electrodes. The physical model of the DBD includes the drift of two ionic species, positive and negative, and the Poisson equation for the electric potential distribution. The spatio-temporal distribution of the electric field, the space charge density in the ambient air, and the surface charge density on the dielectric layer have been determined. The time average electric body force was entered into the air flow model, which was solved using the Spalart–Allmaras turbulence technique. The simulation of the air flow was performed for the free-stream velocities between 5 m/s and 20 m/s (Reynolds numbers 1.65 × 105–6.61 × 105 based on the chord length). The results of computations show the effect of the electrohydrodynamic actuation on the flow pattern, the lift and drag coefficients, the pressure coefficient, and the flow fluctuation near the airfoil. The ability of the DBD actuation to effectively control the aerodynamic airfoil characteristics has been confirmed, and its limitations for the discussed case have been determined.
25 citations