HADES rotating detonation combustor assembly CAD from my project portfolio
HADES RDC / ASSEMBLY CAD

AEROSPACE ENGINEER IN THE MAKING

Engineering
under
pressure.

I’m Ansh Patel, a Purdue aerospace engineering student turning first principles into propulsion, thermal models, and test-ready hardware.

PURDUE UNIVERSITY / B.S. AAE ’27SCROLL TO EXPLORE

7.62 MW/m²

Predicted RDE wall heat flux

45 → 2 min

Thermal design iteration time

50+

Optical test configurations

3rd

AIAA Region III · 30+ teams

01 / SELECTED WORK

The work behind
the numbers.

From combustion physics to the instruments that make it visible.

02 / EXPERIMENTAL DIAGNOSTICS

Making invisible
flow visible.

Setting up and validating a Self-Aligned Focusing Schlieren system for optical diagnostics at Zucrow Laboratories.

50+

configurations. One validated operating envelope.

  • Schlieren optics
  • High-speed imaging
  • DAQ
Inside the project

THE CHALLENGE

Establish reliable operating parameters for a SAFS optical diagnostic system and prepare instrumentation for supersonic wind-tunnel testing.

MY CONTRIBUTION

Led system setup, integration, and documentation. Designed and executed a test matrix across focal length, Ronchi ruling spacing, and reference-plane positioning to evaluate optical sensitivity.

THE RESULT

Completed more than 50 optical configurations and defined validated operating parameters for the deployment. Set up instrumentation and data acquisition for open-jet crossflow characterization.

Undergraduate Researcher · Purdue Experimental Turbine Aerothermal Laboratory · March 2026–present.
03 / INJECTOR DESIGN

Better mixing.
Less pressure loss.

Using CFD and cold-flow testing to evaluate a Tesla-valve liquid rocket injector against a baseline orifice design.

CFD

Pressure-loss analysis

TEST

Mixing validation

  • ANSYS Fluent
  • FEA
  • Cold-flow testing
Inside the project

THE CHALLENGE

Improve propellant mixing while reducing the pressure demand imposed by the injector.

MY CONTRIBUTION

Designed a Tesla-valve injector and analyzed mixing and pressure drop in ANSYS Fluent. Used cold-flow testing to validate CFD predictions and characterized atomization across five injector geometries.

THE RESULT

The design improved mixing and reduced pressure drop relative to the baseline orifice, connecting simulation results to cold-flow observations.

Injector Configuration Analysis Research · Quantitative test details omitted.

ZUCROW LABORATORIES / OPTICAL DIAGNOSTICS

See the flow.

Schlieren imagery from my experimental work: optical characterization, gas-jet structure, and liquid injection.

EXPERIMENTAL FOOTAGE

Playback slowed for viewing. Test labels and acquisition settings omitted.

Open clip
Grayscale focusing schlieren image from an optical characterization study
01 Optical characterization
Background-subtracted gas jet image with red and blue intensity differences
02 Gas-jet structure
Background-subtracted liquid injection image showing the spray interface
03 Liquid injection

FLOW CHARACTERIZATION / SELECTED ANALYSIS

Following the pressure.

Dimensionless pressure and pressure-derived Mach across two anonymized conditions. Exact axial coordinates and operating settings are withheld.

Anonymized condition A pressure plot showing pressure decreasing along the nozzle, with provisional surface positions noted
CONDITION A

Nondimensional pressure

View plot ↗
Anonymized condition A pressure-derived Mach estimate, with an isentropic assumption and provisional surface positions
CONDITION A

Isentropic Mach estimate

View plot ↗
Anonymized condition B pressure plot showing pressure decreasing along the nozzle, with provisional surface positions noted
CONDITION B

Nondimensional pressure

View plot ↗
Anonymized condition B pressure-derived Mach estimate, with an isentropic assumption and provisional surface positions
CONDITION B

Isentropic Mach estimate

View plot ↗

Surface locations marked with an asterisk remain provisional. Mach values are inferred from pressure under an isentropic assumption. Curves are preserved from the supplied analysis.

Open anonymized plot set

COMPUTATIONAL PROPULSION / MATLAB

Resolving the detonation flow field.

Method-of-characteristics analysis of a rotating detonation flow field, connecting compressible-flow physics with spatial pressure, density, and velocity distributions.

Four normalized MATLAB model fields: static pressure, total pressure, density and speed

Saved laboratory-frame model results. Each field is normalized by its own maximum; the two spatial coordinates are normalized independently. Dimensional operating conditions and geometry are omitted.

Engineering approach

The method of characteristics follows the paths along which information propagates through supersonic flow. Compatibility relations along those paths let the model reconstruct the flow downstream of the detonation.

Analysis focus

Compare pressure, density, and speed distributions to interpret expansion and wave structure. This work uses an existing research solver; the figures show saved numerical output, not experimental measurements or a newly validated simulation.

CO-AUTHOR / AIAA REGION III / THIRD PLACE

Design and Analysis of a Hydrogen-Air RDC for Power Generation Research

A team study of the HADES rotating detonation combustor, combining analytical sizing, CFD, and structural and thermal analysis. I was the responsible engineer for the reduced-order thermal model.

Read the AIAA paper 10.2514/6.2026-116280
↗

DESIGN / COMPONENT STUDIES

From sketch to solid.

Selected component models, presented as visual studies with dimensions and drawing annotations omitted.

CAD / 01

Component housing

VIEW 02 / 02

CAD / 02

Torch ignitor

VIEW 01 / 02

CAD / 03

Mounting frames

VIEW 01 / 02

MORE ENGINEERING, SAME CURIOSITY

04Hall-effect thruster cathodesELECTRIC PROPULSION

Led a 10-member team evaluating more than six cathode material candidates through emission, resistivity, and thermal characterization. Operated a high-vacuum chamber to study performance in simulated space conditions.

Electric Propulsion Engineer · PURPL · August 2024–May 2025

05Truss-braced wing designSTRUCTURES & OPTIMIZATION

Built two truss-braced wing designs using MATLAB and Siemens NX. Analyzed reactions across load cases and optimized strut placement through iterative FEA, reducing weight by more than 30% and checking results against three analytical solutions.

MATLAB · Siemens NX · Finite element analysis

02 / EXPERIENCE

Built in the lab.
Tested in the details.

MAR 2026 — PRESENT

ZUCROW LABORATORIES / PETAL

Undergraduate Researcher

Optical diagnostics, supersonic wind-tunnel instrumentation, and CFD validation at Purdue’s Experimental Turbine Aerothermal Laboratory.

EXPERIMENTAL
DIAGNOSTICS

AUG 2025 — PRESENT

PURDUE UNDERGRADUATE ROCKET PROPULSION LAB

Thermal Systems Lead Engineer

RDE thermal modeling, CNC-machined injector hardware, and combustion and thrust acquisition through NI cDAQ.

PROPULSION
& THERMAL

AUG 2024 — MAY 2025

PURDUE UNDERGRADUATE ROCKET PROPULSION LAB

Electric Propulsion Engineer

Team leadership, cathode material down-selection, and vacuum testing for Hall-effect thruster integration.

ELECTRIC
PROPULSION

03 / THE ENGINEER

A model is only
the beginning.

I’m studying Aeronautical and Astronautical Engineering at Purdue University, with an expected graduation in fall 2027.

My work spans the full engineering loop: model the physics, design the hardware, set up the experiment, and use the data to understand what actually happened.

That has taken me from thermal models for rotating detonation engines to schlieren optics, injector machining, and vacuum-chamber testing. I’m looking for opportunities in propulsion, thermal and fluids, design, and test engineering.

PURDUE / PETALUndergraduate Research AssistantView my official team listing Download my résumé

PURDUE UNIVERSITY

Aeronautical &
Astronautical Engineering

3.72/4.0

GPA

2027

Expected graduation · Fall

Presidential Scholarship
Dean’s List & Semester Honors · 4×
First-generation college student

The toolkit

ANALYZE
ANSYS Fluent & FEA, NASA CEA,
Thermal Desktop
BUILD
Siemens NX, SOLIDWORKS,
CAD/CAM, CNC machining
COMPUTE
MATLAB, Python, C/C++, Git
TEST
NI cDAQ, optical diagnostics,
vacuum operations

04 / NEXT CHAPTER

Propulsion. Thermal & fluids. Design. Test.

Let’s build
what flies.

CAD study

Enlarged CAD study

Geometry preview · dimensional and manufacturing details omitted