Noud P.M Werter, Jurij Sodja, Roeland De Breuker

DOI Number: N/A

Conference number: IFASD-2015-123

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.

Read the full paper here

In Categories: 2. IFASD 2015, Aeroelasticity in Aircraft Design
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.