Rapid supersonic performance estimation for a novel RBCC engine inlet

A method to estimate the supersonic performance of an inlet designed for a rocket based combined cycle engine is developed. This method is to be used for exchange inlet geometry optimisation and as such is able to quickly predict properties that can be used in the design process such as total pressu...

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Bibliographic Details
Published in:Aerospace science and technology 2014-01, Vol.32 (1), p.51-59
Main Authors: Murzionak, A., Etele, J.
Format: Article
Language:English
Subjects:
Compressible flows
shock and detonation phenomena
Detached shocks
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Physics
Rocket based combined cycle
Shock-wave interactions and shock effects
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Summary:A method to estimate the supersonic performance of an inlet designed for a rocket based combined cycle engine is developed. This method is to be used for exchange inlet geometry optimisation and as such is able to quickly predict properties that can be used in the design process such as total pressure loss and mass flow rate. The method is developed using solutions for shocks around sharp cones and estimations of shocks around 2D blunt wedges. The total pressure drop across the estimated shocks as well as the mass flow rate through the exchange inlet are calculated. The estimations for a selected range of free-stream Mach numbers between 1.1 and 7 are compared against numerical finite volume simulations. The predicted mass flow rate does not differ from the numerical simulations by more than 5% for the tested conditions, while the total pressure is predicted to within 10% of finite volume simulations for most of the conditions considered.
ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2013.12.007