Published Paper Details:

The primary investigation in the aerodynamics is to study how the objects fly in the air. Study of flutter analysis is to be considered in the aircraft wing design. In this work the comprehensive study of tapered 3D asymmetrical airfoil wing is focused. There have been the studies which proved to be acceptable by adopting simulation tools and then by experimental validation. In the present study the CAE approach is used to model the aircraft wing according to NACA standards and this model is used for Computational Fluid Dynamics (CFD) analysis. The tapered wing is modeled in CATIA V5 considering NACA 64-210 at the tip and NACA 64-215 at the root. CFD is carried out using ANSYS Fluent R20. The Reynolds number of 3.5 x 106 (30m/s) is considered, which resembles the subsonic speed. The wing considered for the present study is analyzed for the flutter. The wind tunnel experiment is carried out to determine the frequency and amplitude at different angles of attack (AOA) ranging from 0o to 20o. This indicates that the flutter boundary occurs at the lower frequency range for the tapered wing between 0 Hz to 50 Hz. The occurrence of maximum amplitude during lower frequency range certainly not desirable characteristic for the aircraft wing design.