A new shock tube test section has been designed and manufactured for the purpose of increasing the test time and expanding the applications of the shock tube for a multitude of ongoing and future projects. One purpose for the test section extension is to allow for flow visualization of droplets impacted by a shock wave for the interaction of hypersonic vehicles and atmospheric disturbances. Another purpose is to measure behind the incident shock to capture the chemical kinetics for a high-altitude environment and low-pressure, high-temperature space applications. This new test section contains 24 round optical ports for laser spectroscopy for multiple measurement locations in addition to 3 rectangular ports upstream for introducing and imaging droplets in the tube. StanShock was used to simulate the expected test time for the desired temperatures and pressures. This was compared against theoretical calculations of test time as a function of distance and velocity of the shock. The optimal length of the extension of 5 feet was then determined based on minimum required test time and limitations of the physical lab space.
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Vasu Sumathi, Subith
Master of Science in Aerospace Engineering (M.S.A.E.)
College of Engineering and Computer Science
Mechanical and Aerospace Engineering
Aerospace Engineering; Thermofluid Aerodynamic Systems
Length of Campus-only Access
Masters Thesis (Campus-only Access)
Higgs, Jacklyn, "Shock Tube and Gas Dynamic Design Considerations and Implementation for Extended Test Times" (2022). Electronic Theses and Dissertations, 2020-. 1385.
Restricted to the UCF community until December 2023; it will then be open access.