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Application of computational aeroacoustics for the investigation of acoustic diffraction effects along airfoil trailing edges

Grant number: 15/19538-6
Support type:Scholarships in Brazil - Master
Effective date (Start): October 01, 2015
Effective date (End): March 31, 2017
Field of knowledge:Engineering - Aerospace Engineering - Aerodynamics
Principal Investigator:William Roberto Wolf
Grantee:Renato Fuzaro Miotto
Home Institution: Faculdade de Engenharia Mecânica (FEM). Universidade Estadual de Campinas (UNICAMP). Campinas , SP, Brazil
Associated research grant:13/03413-4 - Investigation of noise generation and propagation by aerodynamic configurations using computational aeroacoustics, AP.JP


Airfoil trailing edges represent a fundamental mechanism of aerodynamic noise generation. The physical process of noise generation in an airfoil trailing edge occurs when turbulent structures are advected along the boundary layer, producing velocity fluctuations near the trailing edge. These fluctuations induce further aerodynamic pressure fluctuations that can be scattered by the solid surface of the airfoil. Thus, aerodynamic energy of the flow is converted into acoustic energy propagated in the form of waves which are diffracted at the trailing edge.The study of noise generation in airfoil trailing edges finds application in several problems of scientific and industrial interest such as in aircraft wings, wind turbine blades and fans found in electronic cooling systems. In the first case, the airfoil noise can be generated by deployed slats and flaps for aircraft landing, when these surfaces are extended to provide high lift. Furthermore, jet noise may suffer diffraction along wing trailing edges.With the increasing size of aircraft engines, the jet noise diffraction problem became relevant. In order to reduce fuel consumption in aircraft engines, the industry has chosec to increase the ratio between cold and hot flow regions of the jets. This has approached the engines from the wings to keep a safe distance between the propulsion system and the ground. However, with the engine approach, the jet flow is developed in the proximity to the trailing edge. Furthermore, at takeoff and landing conditions, flaps are extended and interact with the jet flow causing additional noise sources.In this work, computational aeroacoustics will be applied to investigate the diffraction effects of acoustic waves along airfoil trailing edges. In this context, high-fidelity simulations will be used to study the noise sources present in installed jet configurations. In addition, reduced order models will also be developed and used to better understand the noise installation problem.

Scientific publications
(References retrieved automatically from Web of Science and SciELO through information on FAPESP grants and their corresponding numbers as mentioned in the publications by the authors)
MIOTTO, RENATO F.; WOLF, WILLIAM R.; DE SANTANA, LEANDRO D. Leading-Edge Noise Prediction of General Airfoil Profiles with Spanwise-Varying Inflow Conditions. AIAA JOURNAL, v. 56, n. 5, p. 1711-1716, MAY 2018. Web of Science Citations: 2.
MIOTTO, RENATO FUZARO; WOLF, WILLIAM ROBERTO; DE SANTANA, LEANDRO DANTAS. Numerical computation of aeroacoustic transfer functions for realistic airfoils. Journal of Sound and Vibration, v. 407, p. 253-270, OCT 27 2017. Web of Science Citations: 4.
Academic Publications
(References retrieved automatically from State of São Paulo Research Institutions)

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