Examinando por Autor "Giraldo Arias, Santiago"

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    Ítem
    Automatic CFD analysis method for shape optimization
    (Universidad EAFIT, 2007) Giraldo Arias, Santiago; García Ruíz, Manuel Julio
    This project presents an Automatic Computational Fluid Dynamics (CFD) analysis method for shape optimization of an aerodynamic profile -- It begins with an overview of basic concepts on shape optimization, geometry parameterization and objective functions -- It continues with an introduction to the current status of CFD simulation software and types of solvers -- Then expands to optimization based on CFD analysis -- Following, a CFD-based method to optimize aerodynamic profiles under certain restrictions and scenarios is proposed -- Finally, the code implemented to automatically modify a profile bound by a set of control points based on CFD analysis is described -- The project was developed entirely at the EAFIT University’s Applied Mechanics Laboratory in Medellin, Colombia and is part of a collaboration effort in companionship with the University of Aberta in Canada and Los Andes University in Bogota, Colombia
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    Ítem
    Coupled CFD Shape Optimization for aerodynamic profiles
    (Universidad EAFIT, 2015) Giraldo Arias, Santiago; García Ruíz, Manuel Julio
    The present document deals with the optimization of shape of aerodynamic profiles -- The objective is to reduce the drag coefficient on a given profile without penalising the lift coefficient -- A set of control points defining the geometry are passed and parameterized as a B-Spline curve -- These points are modified automatically by means of CFD analysis -- A given shape is defined by an user and a valid volumetric CFD domain is constructed from this planar data and a set of user-defined parameters -- The construction process involves the usage of 2D and 3D meshing algorithms that were coupled into own- code -- The volume of air surrounding the airfoil and mesh quality are also parametrically defined -- Some standard NACA profiles were used by obtaining first its control points in order to test the algorithm -- Navier-Stokes equations were solved for turbulent, steady-state ow of compressible uids using the k-epsilon model and SIMPLE algorithm -- In order to obtain data for the optimization process an utility to extract drag and lift data from the CFD simulation was added -- After a simulation is run drag and lift data are passed to the optimization process -- A gradient-based method using the steepest descent was implemented in order to define the magnitude and direction of the displacement of each control point -- The control points and other parameters defined as the design variables are iteratively modified in order to achieve an optimum -- Preliminary results on conceptual examples show a decrease in drag and a change in geometry that obeys to aerodynamic behavior principles