Numerical investigation of aeroelastic response of wings using unsteady vortex lattice method

Date

2025-4-10

Author

Fırat, Ali Osman

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This thesis presents an in-depth investigation of nonlinear aeroelastic phenomena, specifically focusing on flutter behavior in flexible wing-like structures. A novel computational analysis tool is developed by integrating the Unsteady Vortex Lattice Method (UVLM) for predicting unsteady aerodynamic loads with the Finite Element Method (FEM) for analyzing structural dynamics. The study utilizes comprehensive time-domain simulations to capture the fully nonlinear fluid-structure interactions essential for accurately predicting flutter onset and subsequent aeroelastic response. Initially, the thesis provides an overview of foundational aeroelastic theory and classical frequency-domain methods, emphasizing their shortcomings in capturing complex nonlinear behaviors. Subsequently, the coupling approach between UVLM and FEM is detailed, including mathematical formulations, discretization methods, and iterative solution strategies to ensure accuracy and stability. To validate the developed computational model, well-documented benchmark cases, such as experiments involving two-degree-of-freedom (2-DOF) flat plates in low-speed wind tunnel setups, are analyzed. The numerical results exhibit strong alignment with experimental observations, particularly in predicting critical flutter conditions and aeroelastic responses. Finally, the thesis explores potential applications of the validated analysis method to more complex structural configurations, demonstrating its utility for examining design parameters, stability limits, and flutter mitigation techniques relevant to modern aerospace structures. The outcomes significantly enhance the understanding of nonlinear aeroelastic behavior, providing a robust and efficient computational framework for future aeroelastic analysis and aerospace engineering design applications.

Subject Keywords

Aeroelasticity, Vortex lattice method, Flutter analysis, Thin airfoil

URI

https://hdl.handle.net/11511/114632

Collections

Graduate School of Natural and Applied Sciences, Thesis