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Laboratory of Aeronautical Sciences

Faculty of Mechanical Engineering - University of Campinas

  • Mach number effects on shock-boundary layer interactions over curved surfaces of supersonic turbine cascades

    Jun 11, 2024 Hugo FS Lui, William R Wolf, Tulio R Ricciardi, Datta V Gaitonde

    The effects of inlet Mach number on the unsteadiness of shock-boundary layer interactions (SBLIs) over curved surfaces are investigated for a supersonic turbine cascade using wall-resolved large eddy simulations. Three inlet Mach numbers, 1.85, 2.00, and 2.15 are considered at a chord-based Reynolds number 395000. The curved walls of the airf... Read More

  • Neural networks in feedback for flow analysis and control

    Jun 01, 2024 Tarcísio C Déda, William R Wolf, Scott TM Dawson

    This work presents a methodology for analysis and control of nonlinear fluid systems using neural networks. The approach is demonstrated in four different study cases: the Lorenz system, a modified version of the Kuramoto-Sivashinsky equation, a streamwise-periodic two-dimensional channel flow, and a confined cylinder flow. Neural networks are t... Read More

  • Analysis of transient and intermittent flows using a multidimensional empirical mode decomposition

    Apr 01, 2024 Lucas F de Souza, Renato F Miotto, William R Wolf

    Modal decomposition techniques are important tools for the analysis of unsteady flows and, in order to provide meaningful insights with respect to coherent structures and their characteristic frequencies, the modes must possess a robust spatial support. In this context, although widely used, methods based on singular value decomposition (SVD) ma... Read More

  • Embedded shear layers in turbulent boundary layers of a NACA0012 airfoil at high angles of attack

    Mar 28, 2024 Leandro JO Silva, William R Wolf

    An investigation of turbulent boundary layers (TBLs) is presented for a NACA0012 airfoil at angles of attack 9 and 12 deg. Wall-resolved large eddy simulations (LES) are conducted for a freestream Mach number M= 0. 2 and chord-based Reynolds number R e= 4× 1 0 5, where the boundary layers are tripped near the airfoil leading edge on the suction ... Read More

  • A Study on the Impact of Radiative Heat Transfer for Hypersonic Nonequilibrium Flows over a Cylinder

    Jan 01, 2024 Farney C Moreira, Deborah A Levin, Shubham Thirani, William R Wolf, João Luiz F Azevedo

    Hypersonic flow over a cylinder is modeled using the finite volume method to solve the Navier-Stokes equations, including Park’s two-temperature model for chemical dissociation. The main focus of this work is to carry out a comparative analysis of the thermodynamic nonequilibrium properties along the flow stagnation line, and obtain the infrared... Read More

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