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Latest revision as of 17:01, 11 March 2021
Abstract
The aerospike nozzle represents an interesting technology for Single-Stage-To-Orbit vehicles because of its self-adapting capability. It is possible to get thrust vectoring capabilities in different ways. A straightforward solution consists in applying differential throttling to multiple combustion chambers which feed the nozzle. An alternative technology, which can be used in the presence of a common combustion chamber, is represented by fluidic thrust vectoring which requires the injection of a secondary flow from a slot on the wall. In this work, the flow field in a linear aerospike nozzle is numerically investigated by means of RANS simulations and both differential throttling and shock vectoring are studied. A parametric study is performed to evaluate the potential of the two technologies.
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Published on 11/03/21
Submitted on 11/03/21
Volume 700 - Numerical Methods and Algorithms in Science and Engineering, 2021
DOI: 10.23967/wccm-eccomas.2020.006
Licence: CC BY-NC-SA license
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