100mm-propulsion-system

## 100mm Aerodynamic Propulsion System (Ducted Fan Assembly) ### Project Overview This project features the design and geometric optimization of a high-efficiency 100mm Ducted Fan Propulsion System tailored for unmanned aerial platforms. The design focuses heavily on minimizing aerodynamic drag, maximizing exit velocity, and ensuring precise structural clearances between rotating and stationary assemblies. --- ### Key Design Features & Specifications * **Aerodynamically Optimized Shroud:** Re-engineered from a standard uniform duct to an asymmetric, high-performance profile. It features a generous 20mm radius elliptical inlet bell-mouth to prevent boundary layer separation and flow induction losses, transitioning into a rigid 5mm constant wall section around the rotor. * **Converging Exhaust Nozzle:** The aft section of the main shroud tapers dynamically alongside the tail cone. This reduction in cross-sectional area acts as a converging nozzle, accelerating the exhaust airflow to maximize dynamic thrust. * **Advanced Tail Cone Geometry:** A 50mm tall aerodynamic tail cone featuring a smooth 130mm radius 3-point arc curve to cleanly manage wake vortices and minimize trailing drag. * **Precision Shaft & Bearing Layout:** Designed with strict adherence to fit-and-clearance engineering practices. The rotating elements (Nose Cone and Rotor Hub) feature a tight 4.00mm radius (8mm diameter) bore to grip the central drive shaft securely, while the stationary components (Stator Pod and Tail Cone) feature an expanded 4.50mm radius bore, providing a uniform 0.50mm air clearance to guarantee friction-free operation. * **High-Strength Stator Stage:** Integrates structural exit guide vanes with an optimized 2.00mm extrusion thickness to robustly bridge the core stator pod to the outer shroud while straightening flow swirl. --- ### Engineering Software Utilized * **Dassault Systèmes SolidWorks** (Advanced Parametric Part Modeling, In-Context Assembly Design, Complex Sketch Relations) --- ### Industry Applications This propulsion unit layout is directly applicable to: * **Vertical Take-Off and Landing (VTOL)** unmanned aerial vehicles (UAVs). * **High-Speed Drone Architecture** requiring protected rotor systems and optimized static thrust coefficients. * **Ducted Fan Re-skilling and Benchmarking** for localized fluid flow analysis.