The study of the interaction between a body and a fluid in relative motion is the fundamental problem in aerodynamics.
This is tackled by formulating and implementing advanced theoretical and computational methods with application to the design of the next generation of aircraft, access-to-space systems and to the understanding of the fundamental fluid dynamics mechanisms like turbulent transition and aerodynamically generated noise.
Within the area of computational & theorectical aerodynamics, our research focuses on several key methods in which we have a sustained track-record.
Research in this area focusses on the development of advanced numerical methods to to discretize and solve the Navier-Stokes and Euler equations. This includes: kinetic-based numerical schemes to enhance the consistency with the physics across various Mach and Knudsen regimes, ph-adaptivity and adapt by re-meshing methods in connection with higher-order discretizations (e.g., Discontinuous Galerkin). This is done in the context of the open-source solver SU2 (https://su2code.github.io).
This area covers the formulation of methods to reduce the computational complexity of CFD studies for multi-point analyses. The approach provides cost-effective (up to the limit of real-time computing) yet accurate (in the order of 10% w.r.t. a CFD analysis) solutions. This includes: Reduced Basis (aka Order) methods based on Principal Components Analysis, machine learning and Galerkin-based projection methods for compressible and complex unsteady flow problems.
The aerodynamics of access-to-space system and trans-atmospheric flight is studied by developing methods that take into consideration aspects like thermal and chemical nonequilibrium and the potential loss of validity of Navier-Stokes approach. This includes studies of Jacobian-free methods for potentially complex systems of equations due to finite-rate chemistry and the introduction of kinetic methods. Research in this area includes also the formulation of low-fidelity methods (e.g., modified Newton theory) for re-entry aerothermodynamics.
The methods above contribute to the creation of a highly integrated multi-fidelity platform (from higher-order to low-fidelity methods) for the aerodynamics analysis and design of the next-generation of transonic transport vehicles. This includes: unconventional configurations like blended wings, collaborative fuselages, high aspect ratio wings and the airframe integration of advanced propulsion systems like boundary layer interaction or ultra high by pass ratio concepts.
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