| 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 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 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 Eden-field's displacement thickness delta* 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-epsilon turbulence model. |
