It is vital for an aero-propulsion system to experimentally simulate its performance in a flight condition and to characterize the flow interactions between engine exhaust plume and external flow. A hypersonic and supersonic wind tunnel testing will be implemented with the aid of schlieren-based flow visualization technique. This technique is simple compared to other complex flow visualization technique but is very useful in obtaining both quantitative and qualitative feature of the flowfield. With a test model such as an aircraft nozzle, the information on the plume flowfield will be obtained.
Start Date: 1/10/2022 - End Date: 4/27/2022
Type of Project
10-20 hours hour(s)
The student will be expected to learn a variety of skills and knowledge necessary for flow visualizations in the compressible flowfield: aerodymics, flow visualizations, and wind tunnel operation safety. After gaining knowledge on the wind tunnel operation safety and basic knowledge on the experiment, the researcher will support the students along with the current project. For example, flow visualization on the advanced aircraft inlet configuration and nozzle, and/or those integrated systems will be considered for implementation.
Interested in Working With the Following Programs
For EXCEL URE Students Only
Honors Undergraduate Thesis
Independent Research Credit (4912)
Research and Mentoring Program
Summer Undergraduate Research Fellowship