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) : Zakkay, Victor ; Wang, Chi R

PDF Url : AD0773178

Report Date : Nov 1973

Pagination or Media Count : 124

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.

Descriptors :   *FILM COOLING, *NOSE CONES, ANGLE OF ATTACK, HEAT TRANSFER, HYPERSONIC FLOW, INJECTION, SKIN FRICTION, WIND TUNNEL MODELS

Subject Categories : Guided Missile Traj, Accuracy and Ballistics
      Guided Missile Warheads and Fuzes

Distribution Statement : APPROVED FOR PUBLIC RELEASE