Abstract—This article addresses the problem of a flutter phenomenon and aeroelastic stability of a typical section airplane wing NACA 4412.
The flutter is a dangerous phenomenon which finishes in general by the breaking of the plane, it can be determined as a dynamic instability of the structure.
Flutter appears as a result of an interaction of aerodynamic, elastic and inertial forces, it occurs at a determined flight speed which is called the critical speed of the flutter.
The objective of our study is to calculate the critical speed of flutter by a numerical simulation using the computer code ANSYS CFX 14.0 then the results are validated by testing with a slice wing on a subsonic wind tunnel.
The experimental results are similar to those obtained by the numerical approach.
Index Terms—Aeroelasticity, aerodynamics, ANSYS, critical speed, flutter.
The authors are with the Applied Mechanics Laboratory, Mechanical Engineering Department, the University of Science and Technology of Oran - Mohamed Boudiaf, Algeria (e-mail: halimazerrouki519@gmail.com, boutchichadjilali@gmail.com).
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Cite: Zerrouki Halima and Boutchicha Djilali, "Aeroelastic Analysis of an Aircraft Wing Type NACA 4412 with Reduced Scale," International Journal of Modeling and Optimization vol. 8, no. 4, pp. 241-245, 2018.
