This project implements 2nd-order finite-difference solver for steady-state heat conduction on a non-rectangular domain via area-preserving coordinate transformation. Both direct and iterative solvers (Jacobi and red-black Gauss-Seidel) were developed and benchmarked. Using JAX, a differentiable solver was constructed to infer thermal conductivity κ from real infrared measurement data via gradient-based optimization.
Compressible Euler Solver for 2D Airfoil SimulationThis project writes a 1st-order finite-volume solver for steady-state compressible flow over an airfoil, solving the 2D Euler equations with Roe flux and local time stepping. Custom inflow, outflow, and wall boundary condition fluxes were developed and tested. Simulations on multiple meshes capture pressure coefficient distributions, force coefficients, and Mach contours.
This is a 2D finite-volume solver for incompressible flow over a backward-facing step using a primitive-variable projection method. Velocity fields (u, v) and pressure are solved on a staggered grid with QUICK convection schemes and Jacobi-based pressure correction. Different Re and mesh resolutions are tested to study separation, reattachment, and streamline behavior. The solver also extracts reattachment lengths and pressure recovery patterns.
Designed airplane with 3.0 thrust-to-weight ratio & 4G overload; implemented mini payloads as
mission. ranked Top 10/107 globally
• Led aerodynamic optimization (SolidWorks, xflr5), manufactured foam-carbon-3D-print composite
fuselage
• Streamlined build-test loop by 2 weeks via modular 3D-printed components
UCI Rocket Team (Solid)Designed a payload for a 2m-rocket with 10000ft apogee. Engineered a sysytem to deploy glider as
the payload of rocket, including glider aerodynamic design, secure system and ejection system
• Manufactured glider nose and wing folding mechanism using 3D printing, wing surface wrapping
using carbon fiber sheet, wing surface wrapping using carbon fiber sheet
