Shock-free aerofoil/wing design optimisation via morphing technique: leading and trailing edge deformation
Document typeConference report
Rights accessRestricted access - publisher's policy
The paper investigates the drag reduction of aerofoils and wings using a morphing technique which consists of deforming the leading and trailing edges. It is treated as an optimisation procedure using Evolutionary Algorithms. For the purpose, an in house code - Multi-Objective Genetic Algorithm (MOGA) under High Performance Computing (HPC) environment is used. An Euler code with viscous corrections is used to compute the flow. Baseline design is that of RAE5243. Two test cases are considered; the first one considers a morphing aerofoil/wing design via trailing edge deformation (TED) while the second test uses both leading and trailing edge deformations (LTED) to minimise the total drag. Numerical results show that applying morphing technique on existing aerofoil/wing significantly reduces transonic total drag and improves lift on drag (L/D) value when compared to the baseline design.
CitationLee, D.S. [et al.]. Shock-free aerofoil/wing design optimisation via morphing technique: leading and trailing edge deformation. A: International Conference on Computational Fluid Dynamics. "7th International Conference on Computational Fluid Dynamics". 2012, p. 1-10.