Mean Flow Measurements in a Hypersonic Turbulent Boundary Layer
Abstract
An experimental investigation was carried out to determine the structure of the turbulent boundary layer on the wall of the Jet Propulsion Laboratory Hypersonic Wind Tunnel at a free-stream Mach number of 9.37. Profiles of flow properties were obtained from pitot pressure, static pressure, and total temperature surveys made through the 6 inch thick boundary layer at a station 160 inches from the nozzle throat. Tests were conducted primarily for the following conditions: unit free-stream Reynolds number of 127,000 per inch, corresponding to a Reynolds number based on momentum thickness of 36,800, and a wall to free-stream total temperature ratio of 0.385. A cursory examination of the boundary layer was also made at a unit stream Reynolds number of 67,000. The static pressure measurements, although indicating negligible streamwise variation, revealed the existence of a significant pressure gradient normal to the wall, with the pressure at the wall approximately 45% greater than its free- stream value.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1971
- Accession Number
- AD0886615
Entities
People
- Anthony Demetriades
- Arnold J. Laderman