In this paper, an array of converging-diverging nozzles in parallel is designed to create a highly turbulent, sufficiently mixed flow for the study of turbulent-compressibility effects and assist in the ongoing work of oblique detonation wave (ODW) research. Several nozzle array candidates were designed with varying numbers of nozzles and nozzle sizes and evaluated using computational fluid dynamics to determine which candidate produced the most viable conditions for investigating turbulent compressibility effects. Conditions and design restrictions of the nozzle arrays were tailored to the conditions set in the Hypersonic Wind Tunnel, which is located at the Propulsion and Energy Research Lab at the University of Central Florida.
Bachelor Science in Aerospace Engineering (B.S.A.E.)
College of Engineering and Computer Science
Mechanical and Aerospace Engineering
Length of Campus-only Access
Thornton, Mason R., ""Design and Characterization of Mach 5 Flow for Higly Turbulent Hypersonic Test Facility" (2021). Honors Undergraduate Theses. 893.