Stiffened Wing Panel Optimization Code and Carpet Plot Analysis Using MATLAB

This MATLAB script performs a full parametric analysis and optimization of a stiffened wing panel structure under axial compression—ideal for aerospace and structural engineering applications. The code runs over 1 million iterations across 3, 4, and 5-stiffener configurations, filtering valid designs based on buckling stability, area ratio limits, and minimum weight criteria.

Key Features:

• Automated iteration across stiffener geometries
• Built-in filtering for Euler buckling, area ratios, and weight
• Carpet plot visualization-ready outputs
• Configurable for custom material and panel properties

Perfect for students, researchers, or engineers working on semi-monocoque structures, buckling analysis, or aircraft panel design.

Note: This package includes only the MATLAB code, fully structured and ready for adaptation.