Configuraaaes Aerodinamicas
Mostrando 1-5 de 5 artigos, teses e dissertações.
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1. Advanced turbulence modelling for complex aerospace applications.
The objective of the present research work consists in studying complex aerodynamic flows about typical aerospace configuration, in which turbulence effects play a fundamental role. Such study is performed with an available computational tool that is being developed at CTA/IAE. This is a finite-volume code for unstructured 3-D meshes that solves the compress
Publicado em: 2007
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2. SimulaÃÃo de escoamentos sobre um foguete de sondagem utilizando malhas multiblocos chimera e justapostas.
SimulaÃÃes dos escoamentos aerodinÃmicos sobre um foguete de sondagem tÃpico sÃo apresentadas. FreqÃentemente, os foguetes de sondagem utilizam mais de um conjunto de empenas e necessitam que essas empenas possuam um tamanho razoÃvel. A fim de lidar com esse tipo de configuraÃÃo, o presente trabalho faz uso de uma nova metodologia, que combina simul
Publicado em: 2002
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3. Numerical simulation of three-dimensional flows over aerospace configurations.
The objective of this project is to study three dimensional aerodynamic flows over realistic aerospace configurations, such as the first Brazilian Satellite Launcher (VLS) in its first stage flight form. In order to achieve this objective, computational fluid dynamics and three dimensional adaptive mesh refinement techniques are used. The project focus in fi
Publicado em: 2002
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4. Three-dimensional turbulent flow simulations over aerospace configurations.
The main objective of the present research work consists of studying turbulent flows over typical aerospace configurations. In order to accomplish such goal, a numerical tool to simulate 3-D compressible flows is validated and improved. A finite difference method for structured grids, written for general curvilinear coordinates, is used. A centred spatial di
Publicado em: 2002
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5. An unstructured grid approach to the solution of axisymmetric launch vehicle flows.
A study of the flowfield around axisymmetric launch vehicles in different flight conditions and configurations is performed in this work. Particularly, the VLS second stage flight configuration is analyzed considering the case with and without a propulsive jet in the vehicle base. Among the different cases considered for this configuration there are inviscid
Publicado em: 2001