Design of Aeroelasticity Bench test for NACA0012 Wing Model in the Low Speed Wind Tunnel: Influence of Wing’s Parameters on Flutter Speed

Abstract

The purpose of this study is to calculate the geometries parameters for a wing NACA0012 as well as its materials in order to observe the instability of aeroelasticity such as divergence and flutter phenomenon in the low speed wind tunnel (38 m/s). Approaches used are the theories of aeroelasticity for the static and dynamic instability problem of the wing. The 3D divergence problem is solved first by strip theory to preliminary design the non-tapper wing and the suitable material for static instability at low speed. The V – g method for flutter analysis is carried out to verify the dynamic instability speed designed. A wing with wing chord, wing length is obtained in accordance with the testing section of the considered wind tunnel, and the suitable material is PU. The preliminary design were carried out for the the divergence phenomenon and divergence speeds can be observed at 30.34 m/s [10]. This study continues with the results based on dimensionless analysis of wing’s parameters on flutter speed.