COMPUTATIONAL FLUTTER ANALYSIS ON WIND TUNNEL MODEL OF FIGHTER AIRCRAFT WING WITH CONVENTIONAL AND ANISOGRID STRUCTURAL CONFIGURATIONS

• Main Author: Rizqy Albana, Naufal
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/78766
• Institution: Institut Teknologi Bandung

Flutter occurs due to dynamic instability associated with the interaction of aerodynamic, elastic, and internal forces that can cause structural failure. Therefore, flutter analysis needs to be conducted in aircraft design. Flutter analysis can be conducted on full-scaled model or scaled-down model (wind tunnel model). This research conducts computational structural dynamics and flutter analyses on wind tunnel model of a fighter aircraft wing with conventional and anisogrid structural configurations. Anisogrid structure is a structural design concept in the form of grids that have different mechanical properties in any direction (anisotropic). The wind tunnel model is created based on the geometry from previous studies, the wind tunnel specifications, and the 3D printer’s printing capabilities. Structural dynamic analysis of the wind tunnel model on both structural configurations produces relatively similar natural frequencies and identical mode shapes. Furthermore, the flutter speeds resulted from computational analysis of the wind tunnel model of a fighter aircraft wing with conventional and anisogrid structural configurations are 270 m/s and 280 m/s, respectively.