Title :
Aerodynamic optimization utilizing control theory
Author :
Xiaoliang Zhang ; Junqiang Bai
Author_Institution :
Sch. of Aeronaut., Northwestern Polytech. Univ., Xi´an, China
fDate :
May 31 2014-June 2 2014
Abstract :
This paper presents the method of aerodynamic optimization utilizing control theory, which is also called the adjoint method. The discrete adjoint equations are obtained from an unstructured cell-vortex finite-volume Navier-Stokes solver. The developed adjoint equations solver is verified by comparison of objective sensitivities with finite differences. An aerodynamic optimization system is developed combining the flow solver, adjoint solver, mesh deformation and a gradient-based optimizer. The surface geometry is parameterized using Free Form Deformation (FFD) method and a linear elasticity method is employed for the volume mesh deformation during optimization process. This optimization system is successfully applied to a design case of ONERA M6 transonic wing design.
Keywords :
Navier-Stokes equations; aerodynamics; aerospace components; computational fluid dynamics; design engineering; elasticity; finite difference methods; finite volume methods; gradient methods; mechanical engineering computing; mesh generation; optimisation; transonic flow; vortices; FFD method; ONERA M6 transonic wing design; adjoint equations solver; adjoint method; aerodynamic optimization; computational fluid dynamics; control theory; discrete adjoint equations; finite difference; flow solver; free form deformation method; gradient-based optimizer; linear elasticity method; surface geometry; unstructured cell-vortex finite-volume Navier-Stokes solver; volume mesh deformation; Aerodynamics; Equations; Geometry; Mathematical model; Optimization; Sensitivity; Vectors; Aerodynamic and Adjoint method; Control theory; Optimization;
Conference_Titel :
Control and Decision Conference (2014 CCDC), The 26th Chinese
Conference_Location :
Changsha
Print_ISBN :
978-1-4799-3707-3
DOI :
10.1109/CCDC.2014.6852366
