A CFD study on the structural parameters of NACA 2412 airfoil based air-wing using different composite materials

Abstract Weight is one of the important factors in aerodynamics; we need to reduce the weight of any flying object in order to get the higher lift force. Wight reduction of wing helps us to get better air craft efficiency and high performance. Aluminum alloys are used to make aircraft wing as it is suitable but in this study, we have used few light weighted composite materials for making the aircraft wing and other alloys as well where aluminum is used as the base material and it is mixed with other materials with different proportions for testing the performance. In this study, NACA 2412 airfoil has been chosen and the wing has been designed in Design Modeler 19. The model has been imported to ANSYS Workbench; the static structural analysis has been carried out by putting the required parameters. The objective of the study is to find out which material will be suitable for making aircraft wing among Carbon Fibers, Alpha-Beta Titanium alloy and Al-Zn-Mg alloy.