Forward Swept Wing Static Aeroelasticity

Abstract
In this report, laminated beam theory is used to predict the subcritical static aeroelastic behavior of swept wings constructed on laminated composite materials. Aerodynamic strip theory airloads are used to develop meaningful expressions for the flexible-to-rigid lift ratio and spanwise center of pressure movement of a swept wing as functions of wing aeroelastic parameters for a uniform property wing. A simple matrix method analysis approach to wing subcritical static aeroelastic response is detailed.

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