Heat-Transfer and Static Stability Tests of A 7.5-deg Blunt Cone with Roughness Elements and Sonic Jets to Promote Boundary-Layer Transition at Mach Number 10
Abstract
Aerothermodynamic transition tests were conducted on a 7.5-deg half- angle, blunt cone model to evaluate variations of trip design in promoting boundary-layer transition on a reentry vehicle. Heat-transfer data were obtained using square-shaped roughness elements and sonic jets as boundary-layer trips to determine the effects of (1) trip height, (2) trip spacing, (3) axial trip location, (4) number of rows of trips, (5) staggered trips, and (6) Reynolds number on heat-transfer distributions. Static stability tests were conducted in conjunction with a few selected trip configurations to determine the influence of the boundary-layer trips on the model static stability and axial-force characteristics. The tests were performed at Mach number 10 for angle-of-attack ranges from 0 to 2 deg (heat-transfer data) and from -7.5 to 7.5 deg (static stability data). Free-stream Reynolds number, based on total model length, was varied from 1.5 to 6.2 million. Selected heat-transfer and static stability data are presented to illustrate the effects of configuration variables and Reynolds number.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1977
- Accession Number
- ADB016942
Entities
People
- D. B. Carver
- J. T. Best Jr.
- W. R. Martindale
Organizations
- Arnold Engineering Development Complex