Design, Static Structural and Modal Analysis of Aircraft Wing (Naca 4412) Using Anasys Workbench 14.5
Journal Title: International Journal of Engineering and Science Invention - Year 2018, Vol 7, Issue 12
Abstract
The weight reduction of a wing is very important to improve the efficiency of an air craft. out of all the parts of an air craft the wings plays a major role in getting high performance. usually the aluminium aircraft wing structure will suitable , but in my present work some composite materials, in which aluminium as base material and mixed with some other materials at different proportions were selected for the design of wings and also tested for its performance. A suitable wing profile NACA 4412 is selected and modeled in CATIAV5 R20. The generated wing profile is imported to ANSYS WORKBENCH. Static structural analysis is carried out in ANSYS by inputting the properties of the optimum specimen which are obtained experimentally. The main purpose of this project is to find out which material out of the following three such as AL-Zn-Mg alloy 7178, ALUMINIUM LITHIUM A8090 and ALPHA- BETA TITANIUM ALLOY is best suited for making wing of flight.
Authors and Affiliations
Ramindla Praveen, Elumagandla surendar, K shyam kumar
Keywords
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