Project Overview
This project focused on the aerodynamic modeling, numerical analysis, and CAD synthesis of optimal rotor blade geometries for multirotor drone systems. By combining numerical mathematical computing in MATLAB with parametric 3D CAD modeling in SolidWorks, the goal was to maximize static thrust generation and lift-to-drag efficiency while reducing acoustic turbulence.
Custom MATLAB algorithms were developed to implement Blade Element Momentum (BEM) theory. The mathematical solver evaluated local angle-of-attack distributions, lift/drag coefficients along discretized blade segments, and optimal chord length tapers from root to tip. The algorithm iteratively calculated pitch twist distribution angles to maintain uniform aerodynamic loading across high-RPM operating conditions.
The resulting mathematical coordinates were imported into SolidWorks using parametric equation curves and lofted airfoil cross-sections. Structural stress analysis and centrifugal load simulations were performed to validate material integrity at peak operational velocity, resulting in a high-efficiency propeller design ready for rapid prototyping.
Key Contributions
- Formulated custom MATLAB computational scripts implementing Blade Element Momentum (BEM) theory to optimize blade pitch twist and chord taper distributions.
- Modeled high-efficiency 3D rotor geometry in SolidWorks by lofting mathematical airfoil cross-sections from generated coordinate point clouds.
- Conducted stress and centrifugal force simulations to ensure mechanical durability and dynamic balance under high-RPM operating loads.