Optimization of a lifting system with a given platform in supersonic flow

Author

Ignatieva, A.V. ; Silantiev, V.A.

Author_Institution

Siberian Aeronaut. Res. Inst., Novosibirsk, Russia

Volume

1

fYear

1999

fDate

1999

Firstpage

82

Abstract

Optimization problem of the surface in a complex lifting system is solved in the framework of a linear theory. Variations of local angles of attack are founded which lead to the reduction of induced-wave drag coefficient at given values of lift coefficient and pitching moment, volume and wing thickness. The optimization problem is solved by variation method, whose base is the reversibility theorem. The obtained results showed the advisability of the optimization problem solution not only for the wing alone, but for a configuration containing all lifting surfaces and fuselage. A comparison is carried out with the calculation of a three-dimensional configuration by the MacCormack finite-difference method

Keywords

aerodynamics; aircraft; drag reduction; optimisation; supersonic flow; variational techniques; Concord; Concorde; MacCormack finite-difference method; aircraft drag; complex lifting system; fuselage; induced-wave drag coefficient reduction; lift coefficient; lifting system optimisation; linear theory framework; local angles of attack variations; pitching moment; reversibility theorem; supersonic aircraft; supersonic flow; surface optimisation; three-dimensional configuration; variation method; wing thickness; Aerodynamics; Aircraft; Application software; Design automation; Equations; Finite difference methods; Fluid flow; Lagrangian functions; Optimization methods;

fLanguage

English

Publisher

ieee

Conference_Titel

Science and Technology, 1999. KORUS '99. Proceedings. The Third Russian-Korean International Symposium on

Conference_Location

Novosibirsk

Print_ISBN

0-7803-5729-9

Type

conf

DOI

10.1109/KORUS.1999.875873

Filename

875873