Development of an optimization framework for a circulation control airfoil with a morphing trailing edge
Date of Award
Master of Science in Engineering (MSE)
Mechanical and Aerospace Engineering
Wing warping (Aerodynamics), Trailing edges (Aerodynamics), Airplanes--Control surfaces
This research investigates the impact of a circulation control airfoil with a deformable trailing edge, on lift-to-drag ratio, to evaluate the use of deformation to reduce the momentum coefficient of blowing (C μ). A framework is developed for optimization of the deformable trailing edge on a NACA 0015 consisting of: a developed parametrization method (Chord Limited discontinuous Morphing Class Shape Transformation), Bayesian optimization, an objective function (Cl ⁄ Cd), a developed communication method, and a Computational Fluid Dynamics solver (Ansys Fluent). The optimization takes place over five blowing actuations (C μ=0, 0.05, 0.1, 0.15, and 0.2) and two angles of attack (AoA=0o and 7o). The geometric results from the optimization show good convergence in terms of deflection and curvature. Results indicate that, for no blowing actuation, optimization at AoA=7o performs better than AoA=0o. However, with blowing actuation, optimization results in significantly higher Cl ⁄ Cd with AoA=0o, especially at blowing coefficient of C μ=0.05.
Schweikert, Micajah, "Development of an optimization framework for a circulation control airfoil with a morphing trailing edge" (2022). Theses. 393.