Rishabh Choudhury  , Victor F. Villace  , Johan Steelant  , David Buttsworth , Marco Marini  and Sara Di Benedetto

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_1100813

An aerothermodynamic analysis was carried out for the HEXAFLY-INT hypersonic glider incorporating geometrical elements such as wing-aileron gap, aileron hinge cavities, and communication antennas. These features exhibited localised changes to the flow-field affecting local heat-transfer distribution and control surface efficiency as compared to the existing “clean” aerodynamic (AEDB) model. The methodology presented in this paper is based on a reduced flow field domain to study the wing-aileron region and telecommunication antennas of the flight vehicle in more detail by adding the necessary geometrical complexities to the numerical model, while minimising the associated computational costs. This methodology was verified through a comparison with the full domain simulations at cruise fight conditions of the aerodynamic model. Although the aerodynamic coefficients or hinge moments are from a global perspective not severely altered by the presence of openings or cavities, the local heat transfer rates are higher for the detailed model. Modifications to the original flight configuration were suggested that minimise the heat-transfer rates and create a flow field closer to the aerodynamic model.

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In Categories: Guidance & Control Systems, High-Speed Aerodynamics and Aerothermodynamics, High-Speed Missions and Vehicles, HiSST 2018, Hypersonic Aerodynamics, Thermal Protection Systems
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