Adaptive unstructured grid computation for planar flow in a ram accelerator

Morales, Marcelo M.; Migueis, C.; Bastos-Netto, D.; Azevedo, João Luiz F.; Minucci, M. A. S.

doi:10.2514/6.1998-3451

Cited by 2 publications

(2 citation statements)

References 10 publications

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“…The need to simulate the flow in a broad range of velocities, i.e., from the low subsonic to the supersonic regime lead to the use of the Euler Equations in which the density and the energy terms are replaced by the pressure and temperature, with the assistance of the equation of state [1].…”

Section: Theoretical Formulationmentioning

confidence: 99%

Numerical simulation of a liquid propellant rocket motor

et al. 2001

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This work presents a numerical simulation of the flow field in a liquid propellant rocket engine chamber and exit nozzle using techniques to allow the results to be taken as starting points for designing those propulsive systems. This was done using a Finite Volume method simulating the different flow regimes which usually take place in those systems. As the flow field has regions ranging from the low subsonic to the supersonic regimes, the numerical code used, initially developed for compressible flows only, was modified to work proficiently in the whole velocity range. It is well known that codes have been developed in CFD, for either compressible or incompressible flows, the joint treatment of both together being complex even today, given the small number of references available in this area. Here an existing code for compressible flow was used and primitive variables, the pressure, the Cartesian components of the velocity and the temperature instead of the conserved variables were introduced in the Euler and Navier-Stokes equations. This was done to permit the treatment at any Mach number. Unstructured meshes with adaptive refinements were employed here. The convective terms were treated with upwind first and second order methods. The numerical stability was kept with artificial dissipation and in the spatial coverage one used a five stage Runge-Kutta scheme for the Fluid Mechanics and the VODE (Value of Ordinary Differential Equations) scheme along with the Chemkin II in the chemical reacting solution. During the development of this code simulating the flow in a rocket engine, comparison tests were made with several different types of internal and external flows, at different velocities, seeking to establish the confidence level of the techniques being used. These comparisons were done with existing theoretical results and with other codes already validated and well accepted by the CFD community.

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Section: Theoretical Formulationmentioning

confidence: 99%

Numerical simulation of a liquid propellant rocket motor

et al. 2001

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“…A implementação em linguagem de programação Fortran é baseada em código computacional desenvolvido em trabalhos anteriores deste autor (Morales et al, 1997), (Morales et al, 1998). A malha não estruturada foi gerada seguindo o critério de qualidade baseado na ortogonalidade.…”

Section: Discretização Espacialunclassified

Modelagem matemática da fluidodinâmica não-newtoniana e bifásica simplificada da hemólise induzida mecanicamente em sistemas de bombeamento centrífugo de sangue

Morales¹

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Adaptive unstructured grid computation for planar flow in a ram accelerator

Cited by 2 publications

References 10 publications

Numerical simulation of a liquid propellant rocket motor

Numerical simulation of a liquid propellant rocket motor

Modelagem matemática da fluidodinâmica não-newtoniana e bifásica simplificada da hemólise induzida mecanicamente em sistemas de bombeamento centrífugo de sangue

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