CFD Analysis Report: Converging Nozzle and Aerofoil Wing Aerodynamics

This report presents a comprehensive CFD analysis of fluid flow phenomena, encompassing both internal and external flow scenarios. The first part of the report focuses on the analysis of a converging nozzle, designed with a contraction ratio of 36:1. Utilizing Solidworks, a 2D CFD model was created to simulate the flow behavior within the nozzle under varying inlet and outlet pressure conditions. The results, including velocity, pressure, and density profiles, were obtained and validated against analytical calculations using Bernoulli's and continuity equations. The second part of the report shifts to aerodynamic analysis, specifically examining the flow around a NACA 2415 aerofoil wing. Employing ANSYS Fluent, a 2D CFD model was developed to investigate the effects of different angles of attack (4°, 8°, and 12°) on the lift and drag coefficients. The report includes detailed discussions supported by plots and graphs, along with a comparison of the aerofoil's performance data. Furthermore, the study explores the impact of increased flow velocity on the aerodynamic behavior of the wing, presenting velocity, pressure, Mach number, and density contours for analysis. The report concludes with an in-depth discussion of the observations and critical analysis of the flow characteristics under the varied conditions.