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One of our core research areas is propulsion science and engineering for the development of scramjet-powered hypersonic vehicles. We study fundamentals of fluid mechanics and combustion and their applications to the propulsion system. Particularly, scramjet inlet-isolator unstart, streamline-tracing inlet design, flow control, and supersonic combustion are the main focus of our research.
Supersonic Wind Tunnel
A supersonic wind tunnel (free-jet type) is under development. The test section is modulated. Thus, by replacing the nozzle part, the direct connect wind tunnel can be configured as well. The tunnel is currently equipped with a Mach 4.5 nozzle, and other Mach number nozzles are under fabrication. The test time of the tunnel is approximately 1 second. The test section has three optically-accessible windows for flow visualization. The pressure measurements are possible with Kulite sensors and signal conditioners.
To increase the total enthalpy, electrical heaters will be added to the compressed gas supply lines.
Scramjet Unstart
Unstart refers a disgorgement of designed scramjet inlet flows due to mismatched upstream and downstream pressures, improper contraction of the captured flows, etc.
We study fundamentals of scramjet unstart and develop flow control methods to remedy the unstart issue in developing scramjet-powered vehicles.
Streamline-tracing Inlets
For more efficient compression, streamline-tracing inlets have been investigated. In our group, we are particularly interested in developing a scoop-type inlet that could reduce drag and improve efficiency.
We conduct both experimental and computational studies for scoop inlets.
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