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Turbulence measurements in hypersonic boundary layers using constant-temperature anemometry and reynolds stress measurements in hypersonic boundary layers
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Spina, Eric F. |
| Copyright Year | 1995 |
| Description | The primary objective in the two research investigations performed under NASA Langley sponsorship (Turbulence measurements in hypersonic boundary layers using constant temperature anemometry and Reynolds stress measurements in hypersonic boundary layers) has been to increase the understanding of the physics of hypersonic turbulent boundary layers. The study began with an extension of constant-temperature thermal anemometry techniques to a Mach 11 helium flow, including careful examinations of hot-wire construction techniques, system response, and system calibration. This was followed by the application of these techniques to the exploration of a Mach 11 helium turbulent boundary layer (To approximately 290 K). The data that was acquired over the course of more than two years consists of instantaneous streamwise mass flux measurements at a frequency response of about 500 kHz. The data are of exceptional quality in both the time and frequency domain and possess a high degree of repeatability. The data analysis that has been performed to date has added significantly to the body of knowledge on hypersonic turbulence, and the data reduction is continuing. An attempt was then made to extend these thermal anemometry techniques to higher enthalpy flows, starting with a Mach 6 air flow with a stagnation temperature just above that needed to prevent liquefaction (To approximately 475 F). Conventional hot-wire anemometry proved to be inadequate for the selected high-temperature, high dynamic pressure flow, with frequent wire breakage and poor system frequency response. The use of hot-film anemometry has since been investigated for these higher-enthalpy, severe environment flows. The difficulty with using hot-film probes for dynamic (turbulence) measurements is associated with construction limitations and conduction of heat into the film substrate. Work continues under a NASA GSRP grant on the development of a hot film probe that overcomes these shortcomings for hypersonic flows. Each of the research tasks performed during the NASA Langley research grants is discussed separately below. |
| File Size | 454475 |
| Page Count | 7 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960002961 |
| Archival Resource Key | ark:/13960/t3xt0n64r |
| Language | English |
| Publisher Date | 1995-04-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Conductive Heat Transfer Turbulent Flow Stagnation Temperature Enthalpy Flow Measurement Turbulent Boundary Layer Hypersonic Flow Helium High Pressure Reynolds Stress Frequency Response Velocity Measurement Hypersonic Boundary Layer Stress Measurement Hot-film Anemometers Dynamic Pressure Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
