Numerical analysis of axisymmetric scramjet flow fields for optimum pressure sensor location

David, Bailey (2011). Numerical analysis of axisymmetric scramjet flow fields for optimum pressure sensor location B.Sc Thesis, School of Engineering, The University of Queensland.

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Author David, Bailey
Thesis Title Numerical analysis of axisymmetric scramjet flow fields for optimum pressure sensor location
School, Centre or Institute School of Engineering
Institution The University of Queensland
Publication date 2011
Thesis type B.Sc Thesis
Supervisor Russell Boyce
Total pages 47
Language eng
Subjects 0901 Aerospace Engineering
Formatted abstract
This thesis presents a numerical analysis of the inlet of the SCRAMSPACE 1 scramjet and was undertaken to produce a data table of pressure over this inlet. This data table is then to be use to optimise pressure tapings on the vehicles inlet. The scramjet is being developed through a joint project with The University of Queensland leading. It hopes to develop a mature scramjet that will allow for safe, economical and environmentally responsible access to space.

The simulations for this thesis were run over two different free stream flow velocities at a constant dynamic pressure of 53.63kPa. The first flow was Mach 8 at 30km altitude, 1197Pa static pressure and 226.51K static temperature. The second was Mach 12 at 35.6km altitude, 532Pa static pressure and 238.04K static temperature. For both they were simulated at a number of angles of attack ranging from 0° to 5° at a 0.5° increment step. Sadly there was an error in the calculations for these angles and Mach numbers resulting in a 0.4% additional error. The free stream flow was modelled as turbulent viscous flow.

A literature review was undertaken to access the current state of design in this area and to develop a methodology to perform the analysis. Also undertaken was a mesh sensitivity study to find an appropriate mesh resolution which to perform the simulations with. This thesis presents the data found in flow field screen shots and in pressure distribution plots. The simulations themselves were done using an academic solver US3D being developed by the University of Minnesota. Approximately 1 million cells were used to simulate the flow field and on 16 cpus it took 6-8 hours for each simulation to converge.

It was found that the flow separates on the inner surface directed away from the flow between 4.3° and 4.4° for Mach 8 and 1.5° and 2.0° for Mach 12. The next step in research will be to use the data table from this thesis to multi-objective design optimisation approach to locate the optimum locations to place the pressure tapings on the scramjet inlet.
Keyword scramjet
hypersonic flight

Document type: Thesis
Collection: UQ Theses (non-RHD) - UQ staff and students only
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Created: Thu, 25 Sep 2014, 11:16:22 EST by Jessica Minshull on behalf of Scholarly Communication and Digitisation Service