Accession Number : AD0682122

Title :   HEAT TRANSFER TO A CONE SEGMENT MODEL,

Corporate Author : GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CALIF

Personal Author(s) : Streiff,M. L.

Report Date : 26 JUL 1960

Pagination or Media Count : 54

Abstract : The laminar heat transfer to a portion of a 35 degrees half-angle conical surface has been measured at several angles of attack in a rocket wind tunnel. The free stream Mach number was approximately 7, the pressure altitude was about 100,000 ft and the free stream Reynolds number was about 500,000 per foot. The heat transfer along the model centerline was in reasonable agreement with that predicted by conical flow theory. The surface heat transfer near the leading edges was not more than 35% greater than that at the centerline at 20 degrees angle of attack and not more than 10 to 15% greater at 50 degrees angle of attack. (Author)

Descriptors :   (*LIFTING REENTRY VEHICLES, ATMOSPHERE ENTRY), (*ATMOSPHERE ENTRY, HEAT TRANSFER), CONICAL BODIES, ANGLE OF ATTACK, LAMINAR FLOW, WIND TUNNEL MODELS, SPECIFIC HEAT, TRANSPORT PROPERTIES, ENTHALPY, THERMAL INSULATION

Subject Categories : Aerodynamics
      Thermodynamics
      Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE