Accession Number:

ADB062870

Title:

A Demonstration of the Principle of Aeroelastic Tailoring Applied to Forward Swept Wings

Descriptive Note:

Final rept. Feb 1978-Apr 1981,

Corporate Author:

AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Report Date:

1982-01-01

Pagination or Media Count:

138.0

Abstract:

The principle of aeroelastic tailoring with advanced composite materials to increase the divergence speed of a forward swept wing has been demonstrated through low speed wind tunnel tests. The approach was to perform a low cost, fairly simple wind tunnel test on a variable sweep cantilever wing model. Available analytical methods were used and were shown to accurately predict the divergence speed of both aluminum and composite plate structures in the subsonic speed range. Methods were evaluated for predicting the onset of divergence using subcritical wind tunnel data. Results of the analyses and tests are presented.

Subject Categories:

  • Laminates and Composite Materials
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE