• NACA 2412; 0012
• schrenk lift distribution
• induced drag
• wing loading
• steady flight
• blended winglet
• optimized values
• topology
• CFRP
• linear static values
• natural frequency modes.

The configuration of the winglet, with respect to wing dimensions is always a concern during the process of design and fabrication. Winglets being a small structure play an important role in reducing the induced drag in aircraft. A brief overview of wing tip devices and their performance from the manufacturers as well as from airliner’s point of view are initially discussed. The development of the winglet based on the link between wing dimensions and optimization forms the vital part of this thesis.
For this thesis work, which is basically a treatise, we have considered the Airbus A350 – 900 aircraft dimensions for the modelling of the wing. However, winglet dimensions are not the same as the specimen considered, but the optimized versions are accounted. Since, the measurements of the internal structures of the wing-box are maintained confidential by the company, we have considered the topologically acceptable dimensions for the ribs, wing skin, vertical stiffeners and the spars. The study of the thesis is under the constraint of steady flight condition in the cruise phase. All the observations will be taken at an altitude of 35,000ft. The main objective of this treatise is to observe the behavior of the wing and the winglet and to produce the results of static and modal phases, that pave way for the better optimization of the winglet for the future investigations. The secondary objective of the thesis is to deeply understand the concept of the reduction of induced drag by the winglets and the same will be addressed at the inception of the thesis work.
All the work related and required to derive the linear static solution and the modal frequency responses of the wing structure, will be performed during the course of the treatise. The analysis is carried out by the procedure of grouping for obtaining higher conservative results. The values obtained from the results lead us to the adaptive discussions and conclusions, from which the extraction of the innovative ideas for the winglet enhancement will be possible. This thesis work may also be phrased as the origin for the different ways that embark on the improvements, that are essentially possible on the future wing designs of a commercial airliner.