Design of Hypersonic Inlets with High Mixing Efficiencies

Pescod, Ben (2013). Design of Hypersonic Inlets with High Mixing Efficiencies Honours Thesis, School of Engineering, The University of Queensland.

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Author Pescod, Ben
Thesis Title Design of Hypersonic Inlets with High Mixing Efficiencies
School, Centre or Institute School of Engineering
Institution The University of Queensland
Publication date 2013
Thesis type Honours Thesis
Supervisor Stefan Brieschenk
Total pages 48
Language eng
Subjects 0913 Mechanical Engineering
Formatted abstract
A design of a hypersonic inlet with the purpose of creating high fuel-air mixing efficiency has been modelled and simulated using Reynolds Averaged Navier-Stokes (RANS) computational fluid dynamics (CFD) tools based on the SCRAMSPACE I base geometry and flight conditions. The inlet was modelled with delta-wing-shaped chevrons at the leading edge in order to produce a flow field of counter-rotating vortices formed from separating shear layers that would dominate the flow stream and aide in the mixing efficiency. Two alternate designs were modelled, one with no angle of attack to the incoming flow as a comparison for the second whose chevrons are angled by having an ‘inward-facing’ inlet. Each of these designs had a chevron and no-chevron case. The simulation for the inwardfacing geometry with a chevron successfully solved. The other models did not. By comparing the results with literature and hypersonic theory, the flow path generated by the simulation was identical to a no-chevron case; the chevron did not produce any indication of vortical formation. The flow structure could be easily described by the incident shock formed at the leading edge which dominates the incoming flow. It was expected that this model would have the most success in creating vortices. From previous literature, chevrons have been successful in aiding the mixing efficiency in hypersonic flow. Therefore, it is recommended that more models need to be simulated with different chevron geometry to complete this study. Further study recommendations include optimising the chevrons with respect to sweepback angle, angle of attack, slenderness, sharpness, and number of chevrons. Furthermore, non-obtrusive fuel injection should be introduced to measure the effectiveness of the inlet design.
Keyword Hypersonic Inlets

Document type: Thesis
Collection: UQ Theses (non-RHD) - UQ staff and students only
Citation counts: Google Scholar Search Google Scholar
Created: Fri, 11 Dec 2015, 14:34:11 EST by Asma Asrar Qureshi on behalf of Scholarly Communication and Digitisation Service