This multi-phase project analyzed the structural behavior of an aircraft stringer under load using both experimental and computational techniques. Finite Element Analysis (FEA) in ANSYS was used to model stress concentrations and deformation patterns, supported by mesh convergence studies for result accuracy. Destructive tensile testing and strain gauge instrumentation quantified material properties of aluminum 6061, including elastic modulus and yield strength. Photoelasticity offered a visual method to identify critical stress zones, while digital image correlation (DIC) captured full-field displacement and strain. Together, these efforts enabled a detailed investigation into deformation behavior and failure modes, combining practical and theoretical approaches for aerospace structural assessment.