Slender delta wing with conical camber

Bera, Rajendra K (1974) Slender delta wing with conical camber. Journal of Aircraft, 11. pp. 245-247. ISSN 0021-8669

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Abstract

The slenderness assumption of Munk (1924) and Jones (1946), made over and above that of linearization, has often been used to get closed form analytical solutions for wings, bodies, and their combinations. Here, simple expressions are obtained for the aerodynamic characteristics of a slender delta wing, exhibiting an even-order polynomial twist distribution in the spanwise coordinate. Carafoli (1956) derived an integral equation which relates the twist distribution to the pressure distribution. Linearized theory predicts two kinds of solution: one in which a leading edge singularity appears, and the other in which the leading edge experiences zero load.

Item Type: Article
Uncontrolled Keywords: Stress concentration; Mathematical analysis; Delta wings; Exact solutions; Integral equations; Singularities; Aerodynamics; Camber;Aircraft; Wings (aircraft); Linearization; Aerodynamic characteristics;Cambered wings;Conical camber;Delta wings;Slender wings;Aerodynamic drag;Integral equations;Lift
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Users 11 not found.
Date Deposited: 07 Mar 2006
Last Modified: 24 May 2010 04:09
URI: http://nal-ir.nal.res.in/id/eprint/931

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