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 Rong

Report Date : NOV 1973

Pagination or Media Count : 123

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. (Modified author abstract)

Descriptors :   *Nose cones, *Film cooling, Hypersonic flow, Wind tunnel models, Injection, Heat transfer, Angle of attack, Skin friction

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

Distribution Statement : APPROVED FOR PUBLIC RELEASE