Optimization and Design of a Fully Instrumented Mach 12 Nozzle for the X3 Expansion Tube
This paper describes the optimization and design of a new Mach 12 hypersonic nozzle to be used in the X3 expansion tube. The contoured nozzle has been designed and built to accommodate large-scale models and reproduce constant Mach 12 flows to allow for scramjet testing. The requirements for this nozzle were a core flow of at least 300 mm and exit flow angles below 2°. A new optimization process has been developed, using a parallel Nelder-Mead method, and a new shape has been calculated where CFD analysis indicates the design objectives were successfully met. Off-design performance has been evaluated, and the nozzle has been shown to retain good core flow size, Mach number and low flow divergence for different inflow conditions.
This research is supported by an Australian Government Research Training Program (RTP) Scholarship and the Cooperative Research Centre for Space Environment Management (SERC Limited) through the Australian Government’s Cooperative Research Centre Programme. This research was undertaken with the assistance of resources from the National Computational Infrastructure (NCI), which is supported by the Australian Government. The authors finally wish to thank F. De Beurs and N. Duncan for technical assistance with the X3 hardware.
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