Expanding the scramjet operating envelope through oxygen enrichment. This project aims to investigate the benefits of expanding the operating envelope of scramjets to higher altitudes and speeds by enriching their fuel with oxygen. This is expected to enhance the performance and flexibility of hypersonic air-breathing engines designed to form the core of a more reliable and economical access to space system. Expected outcomes of this project are a validated understanding and mapping of how oxyge ....Expanding the scramjet operating envelope through oxygen enrichment. This project aims to investigate the benefits of expanding the operating envelope of scramjets to higher altitudes and speeds by enriching their fuel with oxygen. This is expected to enhance the performance and flexibility of hypersonic air-breathing engines designed to form the core of a more reliable and economical access to space system. Expected outcomes of this project are a validated understanding and mapping of how oxygen enrichment can augment scramjet thrust at high altitudes and speeds, and a performance evaluation of a launch system optimised for this approach. This could provide significant benefits to the performance of reusable, air-breathing launch technology, where Australia is leading the push towards commercialisation.Read moreRead less
Advanced Combustion Modelling for Scramjets and Rotating Detonation Engines. This project will develop new fundamental knowledge and engineering models underpinning air-breathing high speed propulsion engines employing complex hydrocarbon fuels. Extensive data and new physical understanding will be garnered through analysis of direct numerical simulations of supersonic reacting mixing layers including impinging shock waves. That data will be employed to isolate, test and develop computationally ....Advanced Combustion Modelling for Scramjets and Rotating Detonation Engines. This project will develop new fundamental knowledge and engineering models underpinning air-breathing high speed propulsion engines employing complex hydrocarbon fuels. Extensive data and new physical understanding will be garnered through analysis of direct numerical simulations of supersonic reacting mixing layers including impinging shock waves. That data will be employed to isolate, test and develop computationally efficient engineering models that are accurate and efficient for high speed combustion in rotating detonation engines and scramjets. Expected outcomes are knowledge and tools needed to develop practical and effective supersonic propulsion engines for access to space, defence and high speed point-to-point flight.
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Rarefied hypervelocity separated flow in the transitional to continuum regimes. The transition regime for low-density flows is a no-man's-land between free-molecular and continuum flow, where the flow behaves differently to the assumptions typically used for modelling either flow type. Bird's direct Simulation Monte Carlo (DSMC) method is typically thought to be the best way of modelling these flows, but has not produced excellent agreement with previous experiments on low-density separated flow ....Rarefied hypervelocity separated flow in the transitional to continuum regimes. The transition regime for low-density flows is a no-man's-land between free-molecular and continuum flow, where the flow behaves differently to the assumptions typically used for modelling either flow type. Bird's direct Simulation Monte Carlo (DSMC) method is typically thought to be the best way of modelling these flows, but has not produced excellent agreement with previous experiments on low-density separated flows, due to computational limitations and lack of knowledge of the flow's internal energy. This proposal is a blind test of the best current DSMC codes against our experiments and a hypersonic continuum code, with the full internal energy state of the flow experimentally quantified for the first time.Read moreRead less