This project focuses on optimizing the aerostructure of the Bombardier CRJ700’s wing and horizontal stabilizer to minimize fuel consumption during cruise flight. Using OpenAeroStruct, which combines aerodynamic and structural analysis within the OpenMDAO framework, the study evaluates design improvements under both cruise and maneuvering conditions. 
This project focuses on optimizing the NACA 4412 airfoil for transonic flight at Mach 0.87 and an angle of attack of 1.5°, with the goal of maximizing its lift-to-drag ratio. By improving the airfoil’s geometry, it aims to enhance the efficiency of the aircraft wing, reducing drag while maintaining lift in transonic conditions. The study seeks to address the challenges posed by the interaction of subsonic and supersonic flows around the airfoil. 
This study explores optimization techniques using OpenMDAO and OpenAeroStruct, starting with the minimization of the Rosenbrock Function to analyze optimization methods and gradient calculations. A detailed investigation of OpenAeroStruct’s structural model follows, leading to an aerodynamic optimization of an isolated wing, considering design variables such as angle of attack, twist, and chord. The effects of an additional aerodynamic constraint on the optimal solution are also analyzed. 
The OSIRIS-REx mission is NASA’s first asteroid sample-return project, designed to study and collect material from Bennu, providing crucial insights into the early solar system and future space exploration.
TThe study presents two fundamental aspects of compressible fluid dynamics. It examines a shock tube, analyzing flow properties, time discretization, gas variations, and geometry. Additionally, it explores the design of supersonic nozzles, using the method of characteristics to define the geometry of 2D planar and axisymmetric minimum length nozzles. 
The project creates a program that models a supersonic wind tunnel using a quasi-1D approximation, allowing users to calculate key flow parameters, such as Mach number and pressure, along with compressor power requirements, based on input conditions like the test section area and operational scenarios, using real-world flight data, such as from the X-59 aircraft. 
This project investigates the aerodynamic performance of a Co-Flow Jet (CFJ) airfoil using numerical simulations in STAR-CCM+. The CFJ technique, which combines suction and blowing jets along the airfoil surface, is analyzed for its ability to delay flow separation, enhance lift, and reduce drag compared to a baseline airfoil. Simulations are conducted at varying angles of attack and mass flow rates to assess the efficiency of CFJ technology in improving aerodynamic performance. 
This project investigates numerical stability, spatial and temporal discretization errors, and mesh quality in CFD applications. The first part analyzes the 1D convection equation using five different discretization schemes, supported by Von Neumann stability analysis and error evaluation. The second part examines the impact of mesh topology and cell types on the accuracy of a 2D heat transfer problem, using STAR-CCM+ to compare results against an analytical solution. 
This project explores numerical methods in Computational Fluid Dynamics (CFD), focusing on error estimation and the application of the Finite Volume Method. The first part investigates finite difference schemes for derivative approximation, analyzing error decay and accuracy. The second part applies the linearized potential flow equations to compute the 2D flow around a diamond airfoil, evaluating different discretization schemes, solvers, and mesh configurations. 
This project explores two key CFD applications: the simulation of a convergent-divergent nozzle and a shock tube. The first part models the flow through an axisymmetric nozzle, analyzing both inviscid and viscous effects to assess their impact on performance. The second part simulates a shock tube to study shock wave propagation and compressible flow behavior, comparing numerical results with theoretical predictions. 
This report provides a comprehensive analysis of spacecraft recovery systems, emphasising the aerodynamics of the rotor during autorotation. Subjects covered include parachute use in space missions, controlled thrust vector systems, and crucial part recovery for heavy-lift launchers. The study assesses the benefits and drawbacks of recovery methods and suggests a unique rotating wing design for secure landings. It emphasises Mars exploration, evaluates a spinning entry vehicle experimentally, and supports reusable parts. Numerical simulations, Prandtl tip loss functions, and blade element momentum theory are used to investigate aerodynamic characteristics. 
This project compares five configurations of propellants and tank materials based on performance, environmental impact, and cost. The analysis includes RP-1/LOX, LH2/LOX, and UDMH/NTO, with tanks made of aluminum or carbon fiber. Results indicate that carbon fiber is not a viable option due to cost and environmental concerns. RP-1 proved to be the most cost-effective propellant, while LH2 had the lowest environmental impact according to a Life Cycle Assessment. 
This project presents the development of a Smart Trash Can with Odor Neutralization, designed at Instituto Superior Técnico as part of the Product Development and Mechanical Design course. The work encompasses need identification, requirement formulation, and product architecture. It includes mathematical modeling for performance validation, Design for X (DfX) considerations, prototyping, and economic analysis to ensure feasibility and sustainability. 