Stress Analysis on NACA Series Airfoil During Water Impact

Ho, Kah Mann (2018) Stress Analysis on NACA Series Airfoil During Water Impact. Final Year Project (Bachelor), Tunku Abdul Rahman University College.

Text HO KAH MANN - Full Thesis.pdf Restricted to Registered users only Download (3MB)

Abstract

This research deals with the investigation of the stress analysis of the National Advisory Committee for Aeronautics (NACA) series airfoil during water impact for planned ditching incident. This research consists of three different fields of studies, airplane wing structure, Von Karman water impact theory and NACA series airfoil flow characteristic analysis. Wing span and chord length of airplane wing structure model that used in this research is referred to Mohamed Hamdan, et al. Based on the information obtained from Mohamed Hamdan, et al, the wing span length is 5.5 m, chord length at wing root is 2.4 m and wing tip is 0.7 m. Three different NACA series airfoils are selected, NACA 0015, NACA 2412 and NACA 4412 for this research. The selection of NACA series airfoil is based on the research done by other researchers and the flow characteristic for each NACA airfoil has been proven. Third field of study is Von Karman water impact theory, it is the conversion of water impact force acting on the wing. The impact force is based on the rate of change of momentum, buoyancy force and skin friction force. Since the skin friction force is not significant and it is negligible. This method of research for this paper is using SOLIDWORKS Simulation. The aim of this research is to analyze the stress distribution of the airplane wing during water impact and locate the part that having the highest stress.