Here are some projects I've worked on over the years.
Honors thesis research on shock-wave/boundary-layer interactions (SBLI) in hypersonic scramjet inlet flow fields. Running high-fidelity CFD simulations with the MFC compressible flow solver on Brown's Oscar HPC cluster, with SLURM job management and Python post-processing pipelines. Focus on aerothermal load characterization and validation against canonical SBLI cases. Results ongoing — full write-up forthcoming upon thesis completion.
Designed and optimized a converging-diverging exhaust nozzle for a Mach 1.7 civilian transport aircraft. Swept a 1,600-point parameter space across four wall profiles, maximizing cruise thrust coefficient while satisfying FAA takeoff noise constraints. Recommended Witoszynski profile at Aₑ/A* ≈ 2.74.
Developed a modeled a multi-frequency, parallel photonic signal processing architecture for high-dimensional quantum and classical communication systems. Simulating a parallel MZI array for frequency-domain modulation, enabling controlled transfer matrices across RF carriers.
A resin-printed antenna modeled after a seal vibrissae seeking to identify external vortex disturbances in the surrounding environment, while reducing vortex-induced vibrations and minimizing natural frequency disturbances.
Hey y’all, I’m Murphy. I’m a mechanical engineering student at Brown with an electromechanical focus, drawn to the challenge of applying math and physics to solve problems across scales, from dynamic structures to micron-level photonics. I thrive on competition, precision, and collaboration, shaped by my experience as a Division I athlete. Every project is a chance to break down complexity, test ideas under real constraints, and deliver solutions that work. In a world where technology and global priorities are evolving at record speed, I’m committed to bridging the gap between possibility and execution by designing, building, and optimizing systems that make an impact.
Measured lift and drag on a finite-span NACA wing in a subsonic wind tunnel using a two-channel strain gauge balance. Calibrated raw voltage signals to moments, converted to normal and axial forces, then resolved into lift and drag as a function of angle of attack. Results compared against XFLR5 panel-method simulations and finite aspect ratio (FAR) lifting-line theory.
| Step | Method |
|---|---|
| Calibration | Linear fit of voltage → moment using cal.p coefficients |
| Force conversion | Moment arms applied to get normal (N) and axial (A) forces; A zeroed at α = 0° to remove tare drag |
| Lift & drag | L = N·cosα − A·sinα / D = N·sinα + A·cosα |
| Sign check | Axial channel sign auto-corrected if median CD is negative |
| FAR correction | 2D XFLR5 slope corrected to finite AR: a = a₀ / (1 + a₀/πeAR) |
CL and CD curves were plotted three ways: experimental wind tunnel data, XFLR5 panel method + FAR correction, and thin airfoil theory + FAR correction. A drag polar (CL vs CD) and L/D ratio vs angle of attack were also generated. Error bars on normal and axial forces reflect strain gauge signal fluctuations (std dev).
Designed and optimized a converging-diverging exhaust nozzle for a Mach 1.7 civilian transport (Boom Overture class) cruising at 60,000 ft. Used quasi-1D isentropic nozzle theory to sweep a 1,600-point parameter space, balancing two competing objectives: maximizing cruise thrust coefficient CF and limiting takeoff jet velocity to meet FAA noise limits.
| Loss | Penalizes | Profiles affected |
|---|---|---|
| Divergence — Malina correction λ=(1+cosθ)/2 | Large exit angle θ | Conical only; zero for smooth profiles |
| Skin friction — turbulent Schlichting + Van Driest II | Long nozzles (large L/rt) | All profiles |
| Nozzle weight — thin-wall Ti-6Al-4V pressure vessel | Large Ae/A* and long L/rt | All profiles equally |
| Exit non-uniformity — curved throat sonic line | Short nozzles with high throat curvature | Cosine & Cubic only; Witoszynski has κt=0 |
| Profile | Ae/A* | L/rt | CF,R3 | θ_exit |
|---|---|---|---|---|
| Cosine | ~2.7 | ~3.8 | ~1.34 | 0° |
| Cubic | ~2.7 | ~3.5 | ~1.34 | 0° |
| Witoszynski | ~2.7 | ~3.2 | ~1.35 ★ | 0° |
| Mirror n=3 (Iter. 1) | 2.74 | — | 1.347 | ~0° |
Witoszynski profile at Ae/A* ≈ 2.74, L/rt ≈ 3.2. Eliminates both divergence loss (zero exit slope) and the exit non-uniformity penalty (zero throat curvature, κt=0), while its shorter optimal length minimizes friction. Highest net cruise CF of all profiles tested, with takeoff noise and shock feasibility constraints satisfied.
A larger Ae/A* places a stronger normal shock deeper into the diverging section at takeoff — but the subsequent isentropic expansion to a larger exit area reduces exit velocity relative to a smaller nozzle. This counterintuitive result meant the noise and efficiency objectives pointed toward the same area ratio of ~2.74, removing what appeared to be a fundamental design conflict.
Honors thesis investigating shock-wave/boundary-layer interactions (SBLI) in hypersonic scramjet inlet flow fields. The inlet compresses incoming flow through an oblique shock train designed to converge near the cowl lip ("shock-on-lip"), after which the flow passes through an isolator where reflected shocks and adverse pressure gradients can locally separate the boundary layer. Characterizing this SBLI behavior and the resulting aerothermal loads is central to the thesis.
| Area | Description |
|---|---|
| Shock structure | Oblique shock train geometry and shock-on-lip targeting for the inlet compression ramps |
| SBLI characterization | Separation/reattachment behavior where shocks impinge on the developing boundary layer |
| Aerothermal loads | Surface heat flux and pressure loading associated with shock impingement and separation |
| Validation | Comparison against canonical SBLI test cases reported in the literature |
Research is ongoing. High-fidelity runs and validation against canonical SBLI cases are in progress on Oscar; a full write-up will follow upon thesis completion.