Modelling Nozzle throat as Rocket exhaust
Journal Title: International Journal of Modern Engineering Research (IJMER) - Year 2013, Vol 3, Issue 4
Abstract
The ejector mode of rocket-based combined cycles is a concept that has the ability to gain thrust from atmospheric air and reduce fuel consumption and thus reduce the cost of rocket launches. This thesis develops a threedimensional rocket nozzle design that includes the potential for incorporating the ejector effect. The nozzle is designed such that the diverging portion of the nozzle geometry must pass through a gate that is placed on the outer perimeter whose shape does not have to remain axisymmetric, thus creating a void for air intake into the centre of an annular rocket exhaust stream. Viscous effects are included via Edenfield’s displacement thickness δ͓ correlation for turbulent boundary layers. Comparison of computational fluid dynamics to a predefined Mach number distribution is within 1.6% of an inviscid solution and 6.8% for a viscous simulation using the k-ɛ turbulence model.
Authors and Affiliations
Keshava Rao P.
Keywords
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