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The ejector mode of rocket-based combined cycles is a concep t 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 three-dimensional 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 i s placed on the outer perimeter whose shape does not have to remain axisymmetric, thus cr eating a void for air intake into the centre of an annular rocket exhaust stream. Viscous effects are included via Edenfield’s displacement thickness δ ∗ correlation for turbulent boundary layers. Comparison of computational fluid dynamics to a predefined Mach number dist ibution is within 1.6% of an inviscid solution and 6.8% for a viscous simulation using thek-ε turbulence model. For those that have encountered impossible situations and remained dedicated to the cause either as a selfless act or because it was the right thing to do. In their humbleness and humility, they are the true heroes.

Rocket nozzle design with ejector effect potential