Full Flow-Path Design Optimisation of Axisymmetric Scramjets with Premixed Fuel / Air
Scramjets (supersonic combustion ramjets) is a promising hypersonic airbreathing technology that can enable reliable and efficient access-to-space and atmospheric flight at hyper velocity. Scramjet flowfields are inherently highly complex due to substantial coupling of various aerodynamic and aerothermal phenomena. In the present study a full flow-path design optimisation has been conducted for an internal-compression axisymmetric scramjet based on the configuration to be used in the SCRAMSPACE project. Evolutionary algorithms are employed to optimise the full scramjet geometry for maximum net thrust (or minimum overall drag) at Mach 8 in the presence of viscous effects and chemical reactions with a premixed fuel / air inflow assumption. The flowfields for the optimum and baseline geometries have been probed and compared to investigate the key design factors and flow physics. The influence of the design parameters on the engine performance and efficiencies has been examined by evaluating contributions from the individual components at design and off-design points.
axisymmetric scramjet engine full flow path hypersonic airbreathing propulsion design optimisation evolutionary algorithms
Hideaki Ogawa Russell. R. Boyce
Centre for Hypersonics, School of Mechanical and Mining Engineering,The University of Queensland, St. Lucia, Brisbane, QLD 4072, Australia
国际会议
2011年亚太航空航天技术学术会议(APISAT 2011)
澳大利亚
英文
1-10
2011-02-28（万方平台首次上网日期，不代表论文的发表时间）