Hypersonic Flow
Mostrando 13-24 de 28 artigos, teses e dissertações.
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13. Simulação direta molecular da influência de degraus na superfície de veículos na reentrada / Direct molecular simulation of step influence on a reentry vehicle surface
No projeto de veículos hipersônicos, o conhecimento dos fatores que afetam as cargas térmicas e aerodinâmicas que agem na superfície do veículo se torna imperativo. Usualmente, no cálculo das cargas térmicas, a análise assume que o veículo possui um contorno livre de imperfeições. No entanto, descontinuidades estão presentes na superfície de ve
Publicado em: 2009
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14. Simulação direta molecular da influência de degraus na superfície de veículos na reentrada / Direct molecular simulation of step influence on a reentry vehicle surface
No projeto de veículos hipersônicos, o conhecimento dos fatores que afetam as cargas térmicas e aerodinâmicas que agem na superfície do veículo se torna imperativo. Usualmente, no cálculo das cargas térmicas, a análise assume que o veículo possui um contorno livre de imperfeições. No entanto, descontinuidades estão presentes na superfície de ve
Publicado em: 2009
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15. Investigação Experimental da Adição de Energia por Laser em Escoamento Hipersônico de Baixa Densidade
The possibility of reducing the aerodynamic drag and heating of a hypersonic vehicle by addition energy to the air ahead of it is an attractive idea directed toward the hypersonic field. (Mach>5) and can be realized by laser induced plasma generation. In this context, this work presents original results in the experimental investigation of the energy addi
Publicado em: 2008
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16. Gas-surface interaction effect on round leading edge aerothermodynamics
Effects of incomplete surface accommodation in rarefied gas flow have been studied by using the Direct Simulation Monte Carlo (DSMC) method in conjunction with the Cercignani-Lampis-Lord gas surface interaction model. The DSMC calculations examine differences in predictions of aerodynamic forces and heat transfer between full and partial surface accommodatio
Brazilian Journal of Physics. Publicado em: 2007-06
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17. Simulation of blunt leading edge aerothermodynamics in rarefied hypersonic flow
The steady-state aerodynamic characteristics of a new family of blunted leading edges immersed in a high-speed rarefied air flow are examined by using a Direct Simulation Monte Carlo (DSMC) Method. A very detailed description of the flow properties has been presented separately at the vicinity of the nose and adjacent to the afterbody surface of the leading
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2007-06
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18. On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations.
The present work describes the efforts towards the implementation of upwind schemes to simulate supersonic and hypersonic cold gÃs flows. The class of flux vector splitting schemes has been chosen, and the particular methods implemented are the van Leer and Liou schemes. Results for different freestream Mach numbers and mesh topologies are discussed in orde
Publicado em: 2007
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19. Effects of compressibility on aerodynamic surface quantities over low-density hypersonic wedge flow
Hypersonic flow past truncated wedges at zero incidence in thermal non-equilibrium is investigated for a range of Mach number from 5 to 12. The simulations were performed by using a Direct Simulation Monte Carlo (DSMC) Method. The study focuses the attention of designers of hypersonic configurations on the fundamental parameter of bluntness, which can have a
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2006-09
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20. Determinação experimental do fluxo térmico em um corpo rombudo em regime hipersônico com adição de energia à montante / Experimental heat flux to a blunt body in hypersonic flow with upstream laser energy deposition
Devido às altas taxas de transferência de calor que ocorrem em veículos aeroespaciais em vôo hipersônico através da atmosfera densa, e a conseqüente necessidade de sistemas de proteção térmica de massa proibitiva, nos leva ao desenvolvimento de novos métodos de controle de escoamento que permitam o vôo em tal regime. Neste contexto surge o concei
IBICT - Instituto Brasileiro de Informação em Ciência e Tecnologia. Publicado em: 09/12/2005
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21. Verification of the pressure equalisation inside the satellite compartment of the Brazilian satellite launch vehicle
During the atmospheric flight of the Brazilian satellite launch vehicle the pressure inside the satellite compartment should be equalised with the atmospheric pressure. This becomes necessary due to the high pressure differences which result when the vehicle reaches high altitudes with decreasing atmospheric pressures, generating high loads acting on the int
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2005-12
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22. Leading-edge bluntness effects on aerodynamic heating and drag of power law body in low-density hypersonic flow
A numerical study is reported on power law shaped leading edges situated in a rarefied hypersonic flow. The sensitivity of the heat flux and drag coefficient to shape variations of such leading edges is calculated by using a Direct Simulation Monte Carlo method. Calculations show that the stagnation point heating on power law leading edges with finite radius
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2005-09
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23. Comparison between a centered and a flux difference split schemes using unstructured strategy
Products developed at industries, institutes and research centers are expected to have high level of quality and performance, having a minimum waste, which require efficient and robust tools to numerically simulate stringent project conditions with great reliability. In this context, Computational Fluid Dynamics (CFD) plays an important role and the present
Journal of the Brazilian Society of Mechanical Sciences and Engineering. Publicado em: 2005-09
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24. Numerical prediction of nonequilibrium hypersonic flow around Brazilian satellite SARA
Hypersonic flows past Brazilian satellite SARA at zero angle of attack in chemical and thermal nonequilibrium are investigated using an axisymmetric Navier-Stokes solver. The numerical solutions were carried out for freestream conditions equivalent to a typically re-entry trajectory with a range of Mach numbers from 10 to 25. The gas was chemically composed
Brazilian Journal of Physics. Publicado em: 2005-03