CFD analysis of model rocket using the VDI 2206 approach

A model rocket system serves as an excellent example of a mechatronic system, integrating mechanical, electrical, and control components. Computational Fluid Dynamics (CFD) plays a critical role in mechatronic system design by enabling the analysis and optimization of fluid interactions within these integrated systems. In rocket design, the accurate assessment of aerodynamic forces – thrust, weight, drag, and lift – is essential for optimizing performance. CFD analysis is employed to determine the drag coefficient (Cd) and lift coefficient (Cl), both of which contribute to improving the rocket's aerodynamic efficiency. CFD is a powerful tool for evaluating key aerodynamic parameters such as velocity, pressure, and temperature while also identifying and mitigating design flaws to enhance overall performance. This study examines the model rocket system from a mechatronic system design perspective, evaluating three different mesh structures in two- and three-dimensional CFD simulations to determine the most suitable configuration. The accuracy of the mesh depends on factors such as element size, quality metrics (skewness, orthogonal quality), and first-layer thickness. A well-refined mesh that adheres to these criteria significantly enhances the reliability of the simulation results, ensuring more precise aerodynamic analysis and performance optimization. The analysis results obtained in this study indicate that the rocket’s nose cone and the area around the wings are subjected to the highest forces, and that mechanical and structural improvements are needed in these areas.