The design of truly three dimensional scramjet inlets is now possible due to the high availability of CFD software and other computational design tools. The method of stream tracing combined with a mathematical lofting procedure can provide inlet designs with a transition between arbitrary capture and exit shapes. The inlet designed in this project was only considered in the inviscid regime however the performance was well above that of a comparable two dimensional inlet.
There are many choices for the procedure outlined in this project and only a very small number have been investigated. Many other options exist in the regime of nozzle design that could be used when designing an axisymmetric flow field. The investigation of these alternative methods should be undertaken and their applicability to the design of stream traced inlets assessed. Another possible source of performance gains is the possibility to make the bottom of the rectangular capture area the same as that required by the circular throat.
During the course of this project many computational tools have been developed. Some of these are applicable to the general use of the computational facilities within the mechanical engineering department. Other specialized codes has been developed which should allow other researchers to progress through the design cycle much faster than before.