CFD Performance Analysis of a Rocket-Based Combined Cycle (RBCC) Engine
Ashwin
Project Timeline
Jan 2024 - May-2024
OVERVIEW
Culminating Bachelor's Thesis evaluating the aerodynamic and propulsive efficiencies of a novel Rocket-Based Combined Cycle (RBCC) engine for supersonic cruise missile applications. Designed a 3D model in Fusion 360 and conducted rigorous CFD simulations in Ansys Fluent at Mach 2, 3, and 4 to analyze terminal shock location and fluid mixing efficiency, comparing the results against standard ramjet performance.
HighlightS
- Validated CFD methodology by replicating a peer-reviewed ramjet inlet study, matching pressure ratio to back ratio metrics with an error margin of less than 5%.
- Simulated supersonic flow regimes at Mach 2, Mach 3, and Mach 4 using Ansys Fluent to pinpoint terminal shock locations within the inlet.
- Analyzed complex multiphase mixing efficiencies between ram air, rocket plume, and fuel inside the combustion chamber to evaluate overall propulsive performance.
- Processed and visualized aerodynamic data, including vorticity and shockwave behavior, utilizing MATLAB and Ansys.
SKILLS
Computational Fluid Dynamics (CFD)Ansys FluentMATLABAutodesk Fusion 360AerodynamicsSupersonic Flow AnalysisPropulsion Systems
ADDITIONAL CONTENTS
Ashwin
| lowinertia |
Build Your Engineering Portfolio