What is it about?
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.
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Why is it important?
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.
Read the Original
This page is a summary of: Numerical simulation of a liquid propellant rocket motor, Journal of Thermal Science, March 2001, Springer Science + Business Media,
DOI: 10.1007/s11630-001-0015-8.
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