Aero-engine intake aerodynamic design, optimisation and test

随着对带有航空发动机的新型飞行器系统的持续需求，推进系统和机身需要更紧密的集成。随着新的测量方法、计算工具和优化系统的及时发展，可以设想这一设计挑战可以得到解决。博士项目的总体目标是开发、验证和转移复杂航空发动机进气道的空气动力学设计和优化方法。该项目与英国国防科学与技术实验室合作，并由费用和助学金全额资助。

With the continuing need for new air vehicle systems with aero-engines there is a need to the closer integration of the propulsion system and the airframe. With the timely development of new measurement methods, computational tools and optimisation systems it is envisaged that this design challenge can be addressed. The overall aim of the PhD project is to develop, validate and transfer an aerodynamic design and optimisation methodology for complex aero engine intakes. The project is in collaboration with the UK Defence Science and Technology Laboratory and is fully funded for fees and bursary.