Modal Analysis of Aircraft Wing using Ansys

Mechanical Vibration class sample project D
Course Instructor:
M. Ammar Akram (Lecturer MED)
Project by MED students:
Muhammad Usman 20-ME-040
Danial Khan 20-ME-019
M. Wayl Farooq 20-ME-144
Umer Farooq 20-ME-120
In this study, a comprehensive analysis of the modal behavior of an
aircraft wing is presented. The specific wing under investigation is the
swept wing, which features the NACA64A215 structure. To conduct the
analysis, a computer-aided design (CAD) model of the aircraft wing was
downloaded from website. The modal analysis was then performed using
ANSYS WORKBENCH15.0. During the modal analysis, the root chord
of the aircraft wing was fixed, while the tip chord remained free. The
primary objective of this analysis was to determine the five modes of
vibration exhibited by the wing, along with their corresponding natural
frequencies and mode shapes. By fixing one end and leaving the other
end free, the study aimed to understand the wing's dynamic
characteristics and how it responds to various modes of vibration. This
information is crucial for ensuring the wing's integrity and optimizing its
design for enhanced performance and safety.