AeroShape aims to become a fully comprehensive 3D geometry engine for all aircraft components (fuselages, nacelles, etc.), capable of generating geometry representations for various aerodynamic structural analyses, CAD export, and design optimization.

Aerodynamic-structural analysis of a hybrid VTOL transition wing - NACA 0012/2415/4412 spanwise layout, XFLR5 panel method, 9-module Python performance model

Computational aerodynamics laboratory project implementing Hess-Smith panel method and Weissinger lifting-line theory for airfoil and wing analysis

Powered-lift STOL wing design using blown-flap theory, BEMT propeller modeling, and DEP aerodynamic optimization validated through CFD

Industrial aerodynamics case study predicting laminar-to-turbulent boundary-layer transition over a 3-D natural-laminar-flow aircraft wing (AETHER-NLF 25), using the UTSS multi-mechanism transition solver — includes geometry, mesh, solver outputs, figures, experimental validation, and the full report.

3D Vortex Lattice Method (VLM) implementation for a swept, tapered wing with elliptical loading comparison.

🌬️ Analyze aerodynamic properties using panel methods and lifting-line theory, facilitating effective airfoil and wing design for aerospace applications.