Experimental and numerical investigation of flutter phenomenon of an aitcraft wing (NACA 0012)

Abstract

Floating is a dangerous phenomenon for aircrafts and usually ends with plane rupture. It can be used to char-acterize a dynamic instability of the structure. Floating phe-nomenon is usually due to an interaction between aerody-namics, elasticity and inertial forces. It appears at a determi-nate speed of flight called critical floating speed. The aim of the present study is to determine the floating critical speed of an aircraft wing in a subsonic fan by means of experi-mental tests and numerical simulations using the commer-cial Finite Element Analysis package ANSYS CFX. The ob-tained experimental results are in good agreement with those obtained using the numerical approach.