A standard model for the investigation of aerodynamic and aerothermal loads on a re-usable launch vehicle

This paper presents a generic geometry for the study of aerodynamic and aerothermal behaviour relevant to re-usable launchers. The model, denoted RFZ, can be broken down into three subcategories for ascent, re-entry and landing. The vehicle design is presented, outlining simplifications made to retain key features of the vehicle while ensuring a manufacturable and meshable geometry. Computational studies have been performed at a trajectory point reflecting the start of the aerodynamic glide phase for a downrange landing scenario. Results present a trim analysis for two fin deflection settings at three different angles of attack. Additional investigations have been performed analysing the internal flow conditions of the first stage nozzle. Initial calculations suggest that the vehicle is trimmable at the trajectory point investigated. These are the first of many test cases which will look to address common questions with these types of vehicles, including but not limited to, surface heating through retro-propulsion and aerodynamic glide phases, plume-plume and plume-structure interactions, as well as vehicle stability and control. The geometry and results will be made openly available to the research community to promote collaboration in understanding the design challenges associated with re-usable launchers