Development of an optimization framework for a circulation control airfoil with a morphing trailing edge

Author

Micajah Schweikert

Date of Award

2022

Document Type

Thesis

Degree Name

Master of Science in Engineering (MSE)

Department

Mechanical and Aerospace Engineering

Committee Chair

Chang-kwon Kang

Committee Member

Konstantinos Kanistras

Committee Member

Nagavenkat Adurthi

Subject(s)

Wing warping (Aerodynamics), Trailing edges (Aerodynamics), Airplanes--Control surfaces

Abstract

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 (C_l ⁄ C_d), 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=0^o and 7^o). 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=7^o performs better than AoA=0^o. However, with blowing actuation, optimization results in significantly higher C_l ⁄ C_d with AoA=0^o, especially at blowing coefficient of C _μ=0.05.

Recommended Citation

Schweikert, Micajah, "Development of an optimization framework for a circulation control airfoil with a morphing trailing edge" (2022). Theses. 393.
https://louis.uah.edu/uah-theses/393