Multilevel optimization of a supersonic aircraft

Authors:
M. Vázquez;A. Dervieux;B. Koobus
Affiliations:
INRIA, 2004 Route des Lucioles, BP. 93, 06902 Sophia-Antipolis, France;INRIA, 2004 Route des Lucioles, BP. 93, 06902 Sophia-Antipolis, France;Université de Montpellier II, Dept Mathématiques, CC.051 34095 Montpellier Cedex 5, France
Venue:
Finite Elements in Analysis and Design
Year:
2004

Citing 3
Cited 2

Aerodynamic design via control theory

Journal of Scientific Computing
Exact-gradient shape optimization of a 2-D Euler flow

Finite Elements in Analysis and Design
Multilevel parametrization for aerodynamical optimization of 3D shapes

Finite Elements in Analysis and Design

Global optimization, level set dynamics, incomplete sensitivity and regularity control

International Journal of Computational Fluid Dynamics
Reduced-order modeling of transonic flows around an airfoil submitted to small deformations

Journal of Computational Physics

Quantified Score

Hi-index	0.00

Visualization

Abstract

This paper investigates the application of a multilevel preconditioned algorithm for the sonic boom reduction of a supersonic business jet. The optimization algorithm relies on a gradient approach with an adjoint state evaluation. The multi-level preconditioner is designed from an analysis of the gradient regularity loss. The sonic boom reduction is achieved in an indirect way by minimizing what we call the sonic boom downwards emission, which is computed in the near field. Additional aerodynamic performances like lift and drag forces are also guaranteed by including their evaluation in the problem's cost functional. Applications to 3D geometries are presented.