Design And Characterization Of Mach 5 Flow For Higly Turbulent Hypersonic Test Facility

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.

Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

As part of a general tunnel calibration program, an investigation was made of the boundary-layer characteristics at Mach numbers 2, 3, 4, and 5 in the test section of the 12-Inch Supersonic Tunnel (D). The boundary-layer measurements were made at one longitudinal station (near the pitch sector center of rotation) on the centerline of both the flexible plate and sidewall. Measurements were also made at vertical locations on the sidewall between the sidewall centerline and the upper flexible plate. The boundary-layer total thickness, displacement thickness, and momentum thickness, are presented at each Mach number over a Reynolds number range corresponding, in general, to tunnel stagnation pressures between 5 and 60 psia. At each Mach number, the variation of displacement thickness on the side wall between the centerline and the upper flexible plate is presented as is a correlation of the flexible plate displacement thickness with experimental data obtained in other wind tunnels. Velocity profiles and test section Mach numbers are presented to indicate variations with Reynolds number.

This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.

Fluctuating properties of turbulent boundary layers for Mach numbers up to 9.