Curated aerospace dissertation and final-year project ideas across all disciplines — CFD simulation, heat transfer, propulsion efficiency, rocket stability, UAV design, and orbital mission design — each with a defined methodology and deliverable.
A good dissertation or final-year project has three properties: it is technically feasible within the time and resource constraints, it has a measurable outcome you can defend, and it sits at the intersection of what you find interesting and what contributes new knowledge. Browse by discipline below.
A dissertation supervisor will assess: (1) Is the scope achievable in one academic year? (2) Does it use quantitative methods — simulation, experiment, or analysis? (3) Is there a clear research question with a falsifiable answer? (4) Does it build on existing literature rather than reinvent well-known results? Start with a specific, narrow question — broad topics almost always lead to shallow conclusions. "Optimising the fin geometry of a specific sounding rocket for minimum drag" is far stronger than "studying rocket aerodynamics."
Most aerospace projects require MATLAB or Python for analysis, ANSYS Fluent or OpenFOAM for CFD, and SolidWorks or CATIA for geometry. Experimental projects need lab access — wind tunnel, thrust stand, or sensors. Data-heavy projects need statistical analysis skills. All are teachable within a year if you are motivated. AerospaceKit covers MATLAB, CFD, and Arduino instrumentation in depth — use these resources to build the skills your project needs.
Heat transfer is central to propulsion, reentry, and aircraft systems. These projects combine thermal analysis with aerodynamics or structural analysis.
Model the temperature distribution on a first-stage turbine blade with and without film cooling holes at varying blowing ratios. Tools: ANSYS Fluent conjugate heat transfer. Output: cooling effectiveness contours, metal temperature distribution, TBC thickness requirement.
Deliverable: CFD comparison of three hole geometries (cylindrical, fan-shaped, compound angle) vs experimental AGTB data.
Implement the Detra-Kemp-Riddell stagnation heating correlation to compute heat flux at the nose of a blunt-body reentry vehicle as a function of entry velocity and vehicle mass. Size an ablative heat shield (PICA-X material model) for LEO reentry conditions.
Deliverable: MATLAB code, heat flux vs time profile, ablator mass requirement vs entry corridor.
Use the reference enthalpy method to predict laminar and turbulent aerodynamic heating on a flat plate at Mach 5–10, comparing against the Eckert correlation. Investigate the effect of wall cooling (T_wall/T_adiabatic) on skin friction and heat flux.
Deliverable: Validated MATLAB solution compared to Blasius and experimental hypersonic data.
CFD projects are highly valued because they combine theoretical understanding with practical simulation skills that are directly transferable to industry.
Run 2D RANS simulations of NACA 0012, 2412, 4412, and 23012 profiles at angles of attack from -5° to 25° using ANSYS Fluent with k-ω SST. Extract CL, CD, and Cp distributions. Compare against XFOIL and experimental data from NASA TN D-7428.
Deliverable: Polar plots, stall AoA comparison, mesh independence study, validation report.
Simulate the oblique shock system in a 2D mixed-compression inlet at Mach 2.0 and 2.5, investigating total pressure recovery as a function of cowl lip angle. Compare isentropic, single-shock, and two-shock designs against the Oswatitsch criterion.
Deliverable: Mach contours, shock angle measurements, total pressure recovery vs cowl geometry.
Simulate flow over the NACA 4412 aerofoil at 18° AoA (post-stall) using k-ε, k-ω SST, Spalart-Allmaras, and DES turbulence models. Quantify the sensitivity of CL and separated region size to model choice. Compare against available experimental LDA/PIV data.
Deliverable: Turbulence model comparison report, velocity field contours, wake profile comparison.
Build a MATLAB thermodynamic cycle model of a turbofan with variable OPR (20–60:1), BPR (4–15), and TET (1,400–1,900 K). Optimise for minimum specific fuel consumption subject to NOₓ emission and turbine blade temperature constraints.
Deliverable: MATLAB model, Pareto front of SFC vs OPR, sensitivity analysis on component isentropic efficiencies.
Model the regression rate of an HTPB fuel grain as a function of N₂O oxidiser mass flux using the empirical Marxman correlation ṙ = a(G_ox)^n. Simulate the thrust profile and O/F ratio shift over burn duration. Compare neutral vs progressive grain geometries.
Deliverable: MATLAB burn model, thrust curve comparison, O/F shift analysis, sensitivity to grain port diameter.
Model fatigue crack growth in a 7075-T6 aluminium wing spar under a representative gust load spectrum using the Paris law da/dN = C(ΔK)^m. Determine inspection intervals for a damage-tolerance design philosophy using LEFM. Compare plain spar vs spar with crack-stop features.
Deliverable: MATLAB fatigue model, crack growth curves, inspection interval recommendation, fracture mechanics analysis.
Complete a conceptual design of a 5 kg fixed-wing UAV for a defined surveillance mission (3 hours endurance, 100 km range, 2 kg payload). Sizing using Raymer's method: wing loading, thrust-to-weight, aerodynamic efficiency. Aerofoil selection with XFOIL. Stability analysis.
Deliverable: 3-view drawing, mass breakdown, performance estimates, XFOIL aerofoil Cp plots, stability derivatives.
Derive the 6-DOF equations of motion for a quadrotor. Linearise around hover. Design and simulate PID attitude controllers in Simulink. Investigate Ziegler-Nichols tuning vs LQR optimal control. Implement on Arduino/Pixhawk hardware if available.
Deliverable: Simulink model, step response comparison, PID vs LQR performance metrics, hardware test results if applicable.
Design a complete 3U CubeSat (10×10×34 cm, 4 kg max) Earth observation mission to SSO at 550 km. Define mission requirements, ground track repeat cycle, ADCS pointing accuracy, power budget (solar array area, battery sizing), link budget, and propellant budget for attitude control (cold gas thruster). Mass and power allocations to all subsystems.
Deliverable: Full mission design report covering all subsystems, orbital analysis in STK or MATLAB, mass/power/data budget.
Optimise a low-thrust (electric propulsion, Isp = 3,000 s) transfer from LEO to GEO using a simplified Edelbaum spiral model. Compare against Hohmann transfer for time of flight, propellant mass, and eclipse fraction. Implement using MATLAB ode45 with simple feedback steering.
Deliverable: MATLAB trajectory code, ΔV and time comparisons, Isp sensitivity analysis, orbit plot visualisation.
Compute the reentry corridor bounds for a blunt-body capsule entering from LEO. The corridor is bounded below by skip-out (insufficient deceleration) and above by g-load or heating limits. Use Allen-Eggers ballistic entry equations. Compare Apollo Command Module and Dragon 2 reentry parameters against corridor limits.
Deliverable: MATLAB analysis, corridor diagram (flight path angle vs entry velocity), peak g and peak heating comparison.
Navier-Stokes, turbulence models, mesh quality, and ANSYS Fluent workflow — everything needed for a CFD dissertation.
Orbit propagation, panel methods, fatigue crack growth, gas turbine cycle optimisation — all with complete working code.
Aerofoil theory, lift/drag polars, boundary layers, and shock waves — the foundation for aerodynamics dissertation work.
Calculate delta-v, check stability margins, and simulate trajectories — useful starting point for rocket projects.
Gas turbine cycle analysis, bypass ratio optimisation, and specific impulse comparisons for propulsion dissertations.
6-DOF equations of motion, stability derivatives, and LQR control design for flight dynamics projects.
SheCodes Lab teaches Python and C++ from scratch — side by side, free, no experience needed. Includes an engineering module covering NumPy, pandas, ISA models, cost index, and flight data analysis. The same tools used to build the calculators on this site.
shecodeslab.com →