Applications of Active Cooling to Nose Cones
Abstract
The use of film cooling for protecting a nose cone in a hypersonic Mach 6 freestream was investigated experimentally. Tests were performed in a Mach 6 wind tunnel with a contoured axisymmetric nozzle. Downstream and upstream tangential slot injections were applied to investigate the film cooling effectiveness on the surface of a nose cone. Multiple tangential downstream slot injections were used to cool the surface of the blunt nose cone while tangential upstream slot injections were used for the surface cooling of a sharp nose cone. Air at a stagnation temperature of 530 degrees R was used as an injectant. Surface distributions of the heat transfer rates and static pressures were measured for different injection mass flow rates.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1973
- Accession Number
- AD0773178
Entities
People
- Chi R. Wang
- Victor Zakkay
Organizations
- New York University