Design.
Analysis.
Documentation.

CFD analysis of a diverterless supersonic inlet across five parametric bump geometries, run at Mach 1.6. The inlet family sits in the same class used on modern supersonic fighter aircraft. Currently extending into ablative thermal-protection analysis for the same geometry.

Trajectory optimization for a reusable rocket booster across boostback, atmospheric reentry, and the powered landing burn. Drag coefficients are pulled from CFD runs at transonic reentry, max-Q, and subsonic descent and fed back into the trajectory model as a function of Mach number, rather than assumed constant.

Full technical breakdown of a solid propellant rocket motor — cutaway, grain configuration options, and nozzle geometry — modelled and documented to the standard of a design review rather than left as text.

Airframe and component modelling for a UAV platform — geometry built for manufacture and flight testing, not just for a render. Design decisions are informed by hands-on flight-test experience, not made from a desk alone.