About the Project
How should an aircraft wing change shape to achieve the most efficient control?
Aircraft rely on control surfaces such as ailerons and spoilers to manoeuvre, but there are many ways of distributing these surfaces across a wing. Different configurations can generate the same rolling motion while producing very different levels of induced drag and adverse yaw. Future morphing wings introduce even greater freedom by allowing the wing shape itself to change. This creates a fundamental aerodynamic question: what is the optimal way to control a wing, and when does morphing…
provide a genuine advantage over conventional hinged surfaces?
This PhD will address this question by developing a unified aerodynamic framework spanning conventional ailerons, discrete and continuous morphing, spoilers, and flight approaching stall. Starting from the classical lifting-line theory, the student will determine control-surface arrangements that minimise induced drag and adverse yaw during roll. The research will explore how these optima depend on wing geometry, control-surface number and location, control effectiveness, and roll rate.
The project will then move from hinges to morphing. Discretised morphing wings will be optimised and compared with both conventional ailerons and idealised continuously morphing wings. This will answer an important practical question: how much morphing complexity is actually required before meaningful aerodynamic benefits are achieved? Biological flight, including the distributed twist and camber changes used by birds, will provide additional inspiration and physical context.
The research will also go beyond the assumptions of classical linear aerodynamics into the stall regime, investigating how flow separation changes control effectiveness and comparing conventional spoilers with morphing alternatives. Finally, selected theoretical predictions will be tested experimentally using a modular low-speed wing with interchangeable control configurations, supported by force measurements and flow visualisations.
The successful candidate will develop a distinctive combination of skills in aerodynamic theory, mathematical modelling, numerical optimisation, scientific programming, and experimental aerodynamics. The project offers opportunities to publish across several interconnected research themes, present findings at major aerospace conferences, and develop openly reusable methods for preliminary aircraft design. It also provides opportunities for public engagement and collaboration with University aerospace societies through student-led aircraft design and testing.
Ultimately, the project aims to uncover general aerodynamic principles that explain not simply how aircraft control surfaces work, but how they should be designed—providing a bridge from the classical aerodynamics of today’s aircraft to the adaptable wings of future flight.
This project is expected to start in September 2027.
Before you apply: We strongly recommend that you contact the supervisors for this project before you apply.
How to apply: To be considered for this project you must complete a formal application through our online application portal.
When applying, please specify the full title and supervisor/s of the project, details of your previous study, and names and contact details of two referees. You must also upload a Supporting Statement describing the motivation to apply to the project, your CV and transcripts of awarded and in-progress university qualifications. Please note late or incomplete applications will not be considered.
Equality, diversity and inclusion are fundamental to the success of The University of Manchester and central to all our activities. A diverse research community strengthens creativity, productivity and quality, while increasing the societal and economic impact of our work. We welcome applicants from all career paths, backgrounds and sections of the community, regardless of age, disability, ethnicity, gender, gender expression, sexual orientation or transgender status.
We welcome applications from candidates returning to study after a career break or experience in other roles. Flexible study arrangements may be available, including part-time study at 50%, 60% or 80%, subject to the requirements of the project and funder.
Eligibility: The standard academic entry requirement for this PhD is an upper second-class (2:1) honours degree (or international equivalent) in Aerospace Engineering or a closely related discipline OR any upper-second class (2:1) honours degree and a Master’s degree at merit (or international equivalent) in Aerospace Engineering or a closely related discipline.
A strong foundation in aerodynamics, fluid mechanics, and mathematical modelling is desirable, together with passion and interest in aircraft design and flight physics. Experience with scientific programming (e.g., MATLAB or Python), numerical methods, optimisation, computational aerodynamics or experimental fluid mechanics would be advantageous but is not essential, as relevant training will be provided during the project. Candidates should demonstrate strong analytical and problem-solving abilities, enthusiasm for combining theoretical and experimental research, and the ability to communicate scientific results effectively.
This project will remain open until filled.
If your application is submitted by 1st November 2026, you can expect a decision by 18th December 2026.
If your application is submitted by 15th January 2027, you can expect a decision by 30th March 2027.
Self or externally funded students can also be considered for this project.
Funding Notes
Funding for this project covers tuition fees, UKRI minimum annual stipend (currently £21,805/annum) and up to a £2.5k/annum research training support grant for the full duration of the 3.5-year programme.