Accession Number:

AD0773178

Title:

Applications of Active Cooling to Nose Cones

Descriptive Note:

Final rept.

Corporate Author:

NEW YORK UNIV BRONX SCHOOL OF ENGINEERING AND SCIENCE

Personal Author(s):

Report Date:

1973-11-01

Pagination or Media Count:

124.0

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.

Subject Categories:

  • Guided Missile Trajectories, Accuracy and Ballistics
  • Guided Missile Warheads and Fuzes

Distribution Statement:

APPROVED FOR PUBLIC RELEASE