Methodology for a Preliminary Assessment of Hypersonic Aircraft Powered by Liquid Methane

This paper aims at improving existing conceptual design methodologies for high-speed vehicle design in order to enable a preliminary assessment of commercial hypersonic aircraft powered by liquid methane. Notably, the paper introduces new formulations and approaches to the characterization of aircraft configuration, mass breakdown and performance analysis, also focusing on comparison with other fuels, such as liquid hydrogen, for what concerns overall layout, flight efficiency and environmental sustainability impact. An example of application of the method is presented, with focus on a Mach 6 case study. Eventually, the paper provides insights on the opportunities that the liquid methane concept offers compared to hydrogen, also looking at preliminary evaluations related to cost and chemical emissions.