Numerical Simulations of Rocket Combustion Chambers with Supercritical Injection

Martin Seidl (), Roman Keller, Peter Gerlinger and Manfred Aigner
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Martin Seidl: Institut für Verbrennungstechnik der Luft- und Raumfahrt
Roman Keller: Institut für Verbrennungstechnik der Luft- und Raumfahrt
Peter Gerlinger: Institut für Verbrennungstechnik der Luft- und Raumfahrt
Manfred Aigner: Institut für Verbrennungstechnik der Luft- und Raumfahrt

A chapter in High Performance Computing in Science and Engineering ´16, 2016, pp 259-268 from Springer

Abstract: Abstract A thermodynamically consistent model has been implemented into the compressible, implicit combustion code TASCOM3D for the simulation of rocket combustion chambers with supercritical injection. The Soave-Redlich-Kwong equation of state is used, since it offers a good compromise between accuracy and numerical efficiency. Nonreactive and reactive high pressure test cases were simulated for the validation of the implemented model. Generally, a good agreement could be obtained for all test cases.

Date: 2016
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-319-47066-5_18

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DOI: 10.1007/978-3-319-47066-5_18

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