Airfoil Design & Aerodynamics Analysis (CFD)

This project focused on the aerodynamic design and validation of an aircraft wing using computational fluid dynamics. A NACA 2412 airfoil was selected due to its widespread industry use and reliability in low-speed and general aviation applications. The wing was modeled in SolidWorks using imported coordinate data and extruded to a full-scale length of 18 meters, with material properties assigned to reflect aerospace-grade 2024-T3 aluminum.

A time-dependent flow simulation was performed using SolidWorks Flow Simulation to evaluate aerodynamic performance under varying operating conditions. The angle of attack was gradually increased from −8 degrees to 16 degrees over a 30-second interval, allowing lift, drag, and aerodynamic coefficients to be monitored dynamically rather than at a single static condition. Both laminar and turbulent flow regimes were included to improve realism.

Key outputs included lift force, drag force, coefficient of lift, coefficient of drag, and lift-to-drag ratio. Analytical calculations were performed to determine the minimum lift force required to support a 40,000 kg aircraft, and these values were compared against simulation results. The model demonstrated lift forces exceeding the required threshold, confirming the wing’s capability under the simulated conditions. Flow trajectory visualizations further illustrated pressure distribution and airflow behavior around the airfoil, reinforcing the numerical results.

This project demonstrates the application of CFD tools to validate aerodynamic designs prior to physical testing, emphasizing performance verification, efficiency assessment, and design feasibility in aerospace and energy-related industries..