NDLI: Numerical simulation of a liquid propellant rocket motor

Content Provider	Springer Nature Link
Author	Salvador, Nicolas M. C. Morales, Marcelo M. Migueis, Carlos E. S. S. Bastos Netto, Demétrio
Copyright Year	2001
Abstract	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.
Starting Page	83
Ending Page	86
Page Count	4
File Format	PDF
ISSN	10032169
Journal	Journal of Thermal Science
Volume Number	10
Issue Number	1
e-ISSN	1993033X
Language	English
Publisher	Science Press
Publisher Date	2001-01-01
Publisher Place	Beijing
Access Restriction	One Nation One Subscription (ONOS)
Subject Keyword	numerical simulation liquid propellant rocket CFD Mechanics, Fluids, Thermodynamics Engineering Fluid Dynamics Engineering Thermodynamics, Transport Phenomena
Content Type	Text
Resource Type	Article
Subject	Condensed Matter Physics

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