Manuel Stein

W. Jefferson Stroud

Cornelia B. Dexter

A simple structural model of an aircraft wing is used to show the effects of strength (stress) and flutter requirements on the design of minimum-weight aircraft-wing structures. The wing is idealized as an isotropic sandwich plate with a variable cover thickness distribution and a variable depth between covers. Plate theory is used for the structural analysis, and piston theory is used for the unsteady aerodynamics in the flutter analysis. Mathematical programming techniques are used to find the minimum-weight cover thickness distribution which satisfies flutter, strength, and minimum-gage constraints. The method of solution, some sample results, and the computer program used to obtain these results are presented. The results indicate that the cover thickness distribution obtained when designing for the strength requirement alone may be quite different from the cover thickness distribution obtained when designing for either the flutter requirement alone or for both the strength and flutter requirements concurrently. This conclusion emphasizes the need for designing for both flutter and strength from the outset.

Automated Preliminary Design of Simplified Wing Structures to Satisfy Strength and Flutter Requirements

J. Edward Anderson

John M. Hedgepeth

The structural analysis of arbitrary solid cantilever wings by thin-plate theory is reduced to the solution of linear ordinary differential equations by use of the assumption that the chordwise deflections may be expressed in the form of a power series. With the series limited to the first two and the first three terms, the differential equations are solved exactly for several samples of solid delta wings. For cases for which exact solutions to the differential equations cannot be obtained, a numerical procedure is derived. Some experimental data are presented and are found to compare favorably with the present theory.

Deflection and Stress Analysis of Thin Solid Wings of Arbitrary Plan Form with Particular Reference to Delta Wings

John P. Reeder

United States. National Advisory Committee for Aeronautics

Ralph W. Stone

Almer D. Crim

Donald R. Bellman

Franklin A. Diedrich

Franklin K. Moore

Henry A. Pearson

I. Irving Pinkel

Kenneth A. Foss

Franklin W. Diedrich

G. Merritt Preston

Jack C. Humphrey

Gerard J. Pesman

James B. Whitten

John M. Hedgepath

Theodore Male

Charts and Approximate Formulas for the Estimation of Aeroelastic Effects on the Lateral Control of Swept and Unswept Wings

Manuel Stein

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