Design and Stress Analysis of a General Aviation Aircraft Wing
The present study focuses on the design and analysis of a single-engine, propeller-driven general aviation airplane. Initial weight estimation based on the initial sketch and the design mission profile is conducted. The estimated weight and other design parameters are used to define the external geometry of the fuselage, wing and tail. Conic lofting is utilized to render a layout of the design containing the airplane major features. The layout is used to create a three-dimensional model of the aircraft which is placed in a simulation environment accompanied with a computer program to simulate the take-off, climb and cruise segments of the design mission profile. The simulation is deemed a success for the length of the runway modeled was equal to the ground roll and the aircraft did not overshoot it. In addition, static stress analysis of the aircraft wing is also performed using the finite element software package COMSOL where the calculated aerodynamic loads are applied to the wing and appropriate failure theories are used to check for failure probability.