Print Email Facebook Twitter Design and testing of an aeroelastically tailored wing under manoeuvre loading Title Design and testing of an aeroelastically tailored wing under manoeuvre loading Author Werter, N.P.M. Sodja, J. De Breuker, R. Faculty Aerospace Engineering Department Aerospace Structures & Materials Date 2015-06-28 Abstract The design methodology and testing of an aeroelastically tailored wing subjected to manoeuvre loads is presented in this paper. The wing is designed using an aeroelastic analysis tool that is composed of a closely coupled nonlinear beam model and a vortex lattice aerodynamic model. The globally convergent method of moving asymptotes is used to derive an optimal layup design for a constant and variable stiffness wing. In addition a quasiisotropic wing is designed in order to provide baseline reference data. Each wing design is manufactured and tested in the wind tunnel. Lift and root bending moment coefficient and wing deformation have been measured during the test. Measurements were used to validate the numerical results. The agreement between the numerical results and measurements was very good. The comparison yielded an average absolute difference of less than 10% in the case of lift and root bending moment coefficient and an average absolute difference of less than 5% in the case of the wing tip out-of-plane deformation. Subject aeroelasticityaeroelastic tailoringload alleviationdesignexperiment To reference this document use: http://resolver.tudelft.nl/uuid:40a10e00-0fde-44a4-a95b-a74a711f6e13 Source IFASD 2015: 16th International Forum on Aeroelasticity and Structural Dynamics, Saint Petersburg, Russia, 28 June-2 July 2015 Part of collection Institutional Repository Document type conference paper Rights (c) 2015 The Author(s) Files PDF 321833.pdf 1.25 MB Close viewer /islandora/object/uuid:40a10e00-0fde-44a4-a95b-a74a711f6e13/datastream/OBJ/view