Weight Functions Method application on a delta-wing X-31 configuration

Author

Anton, Nicoleta ; Botez, Ruxandra Mihaela

Author_Institution

Dept. de genie de la production automatisee, Ecole de Technol. Super., Montreal, QC, Canada

fYear

2012

fDate

25-28 Oct. 2012

Firstpage

5489

Lastpage

5498

Abstract

The stability analysis of an aircraft configuration is studied using a new system stability method called the weight function method. This new method finds a number of weight functions that are equal to the number of first-order differential equations. This method is applied for longitudinal and lateral motions on a delta-wing aircraft, the X-31, designed to break the “stall barrier”. Aerodynamic coefficients and stability derivatives obtained using the Digital DATCOM code have been validated with the experimental Low-Speed Wind tunnel data obtained using the German-Dutch Wind Tunnel (DNW-NWB). Handling Qualities Methods are used to validate the method proposed in this paper.

Keywords

aerodynamics; aerospace components; aircraft; differential equations; mechanical stability; wind tunnels; German-Dutch wind tunnel; aerodynamic coefficient; aircraft configuration; delta-wing X-31 configuration; delta-wing aircraft; digital DATCOM code; first-order differential equation; lateral motion; longitudinal motion; stability analysis; stability derivative; stall barrier; weight function method; Out of order; DATCOM; aerodynamics; flight dynamics; root locus; stability derivatives; wind tunnel;

fLanguage

English

Publisher

ieee

Conference_Titel

IECON 2012 - 38th Annual Conference on IEEE Industrial Electronics Society

Conference_Location

Montreal, QC

ISSN

1553-572X

Print_ISBN

978-1-4673-2419-9

Electronic_ISBN

1553-572X

Type

conf

DOI

10.1109/IECON.2012.6389516

Filename

6389516