Compressible Flows
Mostrando 1-12 de 35 artigos, teses e dissertações.
-
1. Direct Numerical Simulation of a Compressible Flow and Matrix-Free Analysis of its Instabilities over an Open Cavity
ABSTRACT: This study takes a Jacobian-free approach based on the Arnoldi iteration to present a method to perform hydrodynamic instability analysis based on Direct Numerical Simulations. The method employs high order spatial and temporal discretizations for the flow simulation and has very low requirements of computational time and memory, compared to conven
J. Aerosp. Technol. Manag.. Publicado em: 19/07/2018
-
2. Direct Numerical Simulation Code Validation for Compressible Shear Flows Using Linear Stability Theory
ABSTRACT: In order to simulate compressible shear flow stability and aeroacoustic problems, a numerical code must be able to capture how a baseflow behaves when submitted to small disturbances. If the disturbances are amplified, the flow is unstable. The linear stability theory (LST) provides a framework to obtain information about the growth rate in relatio
J. Aerosp. Technol. Manag.. Publicado em: 07/05/2018
-
3. Further Development and Application of High-Order Spectral Volume Methods for Compressible Flows
Abstract: The present paper investigates the high-order spectral finite volume method with emphasis on applicability aspects for compressible flows. The intent is to improve the understanding and implementation of numerical techniques related to high-order unstructured grid schemes. In that regard, a hierarchical moment limiter and high-order mesh capability
J. Aerosp. Technol. Manag.. Publicado em: 20/07/2017
-
4. A Study of Physical and Numerical Effects of Dissipation on Turbulent Flow Simulations
ABSTRACT: The present work is primarily concerned with studying the effects of artificial dissipation and of certain diffusive terms in the turbulence model formulation on the capability of representing turbulent boundary layer flows. The flows of interest in the present case are assumed to be adequately represented by the compressible Reynolds-averaged Navi
J. Aerosp. Technol. Manag.. Publicado em: 2013-06
-
5. An edge-based unstructured mesh formulation for high speed tridimensional compressible flow simulation
Numerical simulation of realistic compressible flows is very important and requires accurate and flexible tridimensional formulations, which should furthermore be robust and efficient. In this work we describe the development of a computational tool for numerical simulation of inviscid compressible 3-D fluid flow problems. This tool uses as the main building
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2012-03
-
6. Resolução numérica de escoamentos compressíveis empregando um método de partículas livre de malhas e o processamento em paralelo (CUDA) / Numerical resolution of compressible flows employing a mesfree particle method and CUDA
Os métodos numéricos convencionais, baseados em malhas, têm sido amplamente aplicados na resolução de problemas da Dinâmica dos Fluidos Computacional. Entretanto, em problemas de escoamento de fluidos que envolvem superfícies livres, grandes explosões, grandes deformações, descontinuidades, ondas de choque etc., estes métodos podem apresentar algu
IBICT - Instituto Brasileiro de Informação em Ciência e Tecnologia. Publicado em: 25/08/2011
-
7. Sobre o acoplamento fluido-casca utilizando o método dos elementos finitos / On fluid-shell coupling using the finite element method
This work consists of the development of computational tools for nonlinear geometric fluid-shell interaction analysis using the Finite Element Method (FEM). The fluid solver is explicit and its time integration based on characteristics. The computational code is able to simulate the Navier-Stokes equations for compressible flows written in the Eulerian descr
Publicado em: 2011
-
8. High-order unstructured spectral finite volume method for aerodynamic applications.
An implicit finite volume algorithm is developed for higher-order unstructured computation of inviscid compressible flows. The Spectral Finite Volume method is used to achieve high-order spatial discretization of the domain, coupled with a matrix-free LU-SGS algorithm to solve the linear systems arising from implicit time marching of the governing equations,
IBICT - Instituto Brasileiro de Informação em Ciência e Tecnologia. Publicado em: 20/12/2010
-
9. High-order unstructured spectral finite volume method for aerodynamic applications.
An implicit finite volume algorithm is developed for higher-order unstructured computation of inviscid compressible flows. The Spectral Finite Volume method is used to achieve high-order spatial discretization of the domain, coupled with a matrix-free LU-SGS algorithm to solve the linear systems arising from implicit time marching of the governing equations,
IBICT - Instituto Brasileiro de Informação em Ciência e Tecnologia. Publicado em: 20/12/2010
-
10. Verification of numerical solutions for reactive flows in a regeneratively cooled nozzle
Studies for a one-dimensional reactive flow in a LOX/LH2-rocket engine nozzle with regenerative cooling system were performed, using the finite volume method, co-located grids and the GCI estimator for the discretization errors evaluation. Five physical models were employed: two one-species ones (with constant and with variable thermophysical properties) and
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2010-09
-
11. Numerical investigation of the three-dimensional secondary instabilities in the time-developing compressible mixing layer
Mixing layers are present in very different types of physical situations such as atmospheric flows, aerodynamics and combustion. It is, therefore, a well researched subject, but there are aspects that require further studies. Here the instability of two-and three-dimensional perturbations in the compressible mixing layer was investigated by numerical simulat
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2009-06
-
12. Unsteady aerodynamic coefficients obtained by a compressible vortex lattice method.
Unsteady solutions for the aerodynamic coefficients of a thin airfoil in compressible subsonic or supersonic flows are studied. The lift, the pitch moment, and pressure coefficients are obtained numerically for the following motions: the indicial response (unit step function) of the airfoil, i.e., a sudden change in the angle of attack; a thin airfoil penetr
Publicado em: 2009