On developing efficient parametric geometry models for waverider-based hypersonic aircraft

• Main Author: Kontogiannis, Konstantinos
• Other Authors: Sobester, Andras
• Published: University of Southampton 2017
• Online Access: https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.741676

This work is focused on tackling the high dimensionality and complex nature of waverider based high speed aircraft design through the development of effective and efficiently parameterized parametric geometry models. The first part of the work is focused on the parameterization and handling of waverider forebody geometries. Different design approaches and a novel design method are presented, each offering direct control of different aspects of the geometry. This can be utilized to directly implement any design constraints or to enable straightforward interfacing with additional geometry components. The new three-dimensional leading edge waverider design method that is proposed is a step away from inverse and one towards direct waverider design. A series of requirements for designing valid three-dimensional leading edge curves are also highlighted. A method to compare different parameterization schemes in order to avoid over or under-parameterizing the geometries and assist in deciding on the number of degrees of freedom and control points for the design-driving curves of the inverse design methods is also presented. This enables the designer to make better educated decisions during the parametric model development phase and when parameterizing hypersonic-design-specific components for which we have limited experience and detailed data in the literature. Complementing the waverider forebody component of the aircraft are a series of blunt leading edge shape formulations. Their effectiveness and efficiency compared to other blunting approaches is highlighted. They are suitable for generating blunt shapes for any wedge-like geometry and they can also be used for inlet cowls, sidewalls, control surfaces, etc. They also offer second order continuity at the interface between the blunt part and the original geometry, which can have a favourable effect on the receptivity and turbulent transition mechanism. Finally, a parametric geometry model development framework consisting of a revised aerodynamic design process that involves design loops to better tune the parametric model, and a geometry engine developed to enable these early design loops, is presented. This is complimented by a number of implementation specific findings and proposed features such as an interactive GUI with real-time updates and dynamically controlled resolution of the generated geometries.