Connecting flow physics to component performance
We study flow through compressors, turbines, airfoils, and cascades to understand the mechanisms that govern aerodynamic performance and losses. Our scope includes compressible boundary layers, shocks, separation, and transition relevant to aerospace and defense applications.
- Corner separation and endwall flow in compressor cascades
- Compressor stall suppression through casing treatments
- Combustor–turbine interactions and unsteady flow
- Compressible boundary layers and shocks over airfoils and cascades
- Flow fluctuations and aerodynamic noise generation
Research experience and recent publications
Public records from Turbo Expo 2018 and 2020 and the 2018 Stanford CTR Summer Program cover cascade separation, transverse shear and endwall flow, and combustor–turbine interactions. We also introduce the PI’s prior industrial research experience in engine and HVAC aeroacoustics.
Our 2025 hydrogen compressor paper examines flow and noise in the valve, discharge jacket, and outlet pipe of a positive-displacement compressor. It provides a related example of unsteady internal-flow analysis.
Engineering questions
We examine blade loading, pressure rise, efficiency and losses, stall, pressure fluctuations, and noise sources. See the public research record and publications for the supporting work and its dates.
Inlet nonuniformity and compressor performance
A 2024 conference study of NASA Rotor 67 compared RANS predictions using nonuniform inlet dynamic pressure derived from turbulent-boundary-layer LES. Even with the same mean total pressure, a uniform inlet can overpredict performance, especially at higher span. Sugyeom Kim and Deokjin Jo are credited as student coauthors in the conference record.
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