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Development of a reduced-order aerodynamic model for the analysis of the aeroelastic response of airfoils at high angles of attack

Grant number: 21/09224-5
Support type:Scholarships in Brazil - Doctorate (Direct)
Effective date (Start): March 01, 2022
Effective date (End): February 29, 2024
Field of knowledge:Engineering - Aerospace Engineering - Aerodynamics
Principal researcher:Flávio Donizeti Marques
Grantee:George Lucas Souto Torres
Home Institution: Escola de Engenharia de São Carlos (EESC). Universidade de São Paulo (USP). São Carlos , SP, Brazil

Abstract

Vortex shedding in the flow during unsteady aerodynamic phenomena gives rise to deviations from the expected static behavior. This type of event can be harmful as it can cause undesired vibrations and load spikes. In this sense, the appearance and development of leading-edge vortices are of great interest to the field of unsteady aerodynamics. In the LDVM model (LESP-modulated discrete vortex method), an intermittent vortex shedding criterion at the leading edge, governed by the maximum suction supported at that point, is introduced. When the thin airfoil theory is applied, this Leading-Edge Suction Parameter (LESP) is related to the first term of the Fourier series that represents the vorticity distribution of the airfoil through the chord. Despite its robustness, the model fails when a significant flow separation at the trailing edge occurs. In this sense, the UTM model is suitable to simulate kinematics where the separation only occurs at the trailing edge. This research project aims to develop a reduced-order aerodynamic model through the LDVM and UTM models, which can estimate the aerodynamic loads acting on an airfoil at high angles of attack. The validation of the aerodynamic model will be carried out through comparisons with CFD simulations, followed by the analysis of the aeroelastic response. (AU)

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