Accession Number : AD0664253

Title :   EXPERIMENTAL STUDIES OF A LAMINAR HYPERSONIC CONE WAKE,

Corporate Author : PRINCETON UNIV N J GAS DYNAMICS LAB

Personal Author(s) : Murman,Earll M.

Report Date : NOV 1967

Pagination or Media Count : 71

Abstract : An experiment was conducted which is representative of the wake flow for a hypersonic Mach number-low Reynolds number flight condition. A 10 degree half-angle sharp cone was magnetically suspended in a Mach sixteen helium stream. A conventional hypersonic wind tunnel of long test duration generated the flow and provided the basis for an experiment which was purely fluid mechanical in nature. The cone model was at the adiabatic wall temperature and zero angle of attach. The free stream Reynolds number based on the one inch cone base diameter was 121,000. The base pressure was higher than the freestream ambient level. There was no appreciable extent of constant axial static pressure in the base flow region. A maximum axial static pressure (freestream conditions) of 2.4 was found at Z = 0.75 D. Downstream of this, the static pressure decreased to near freestream level at about Z = 5D. A rapid acceleration of the axial flow in the near wake was observed downstream of the wake stagnation point. At Z = 5D, the axial velocity returned to about 70-80% of the freestream value. The trailing shock wave origin is near Z = 1D, and it emerges from the viscous wake around Z = 3D. The spatial extent of the recirculation region, recompression zone, wake thickness, and overall near wake region were on the order of the model base diameter. (Author)

Descriptors :   (*HYPERSONIC TEST VEHICLES, WAKE), WIND TUNNEL MODELS, LAMINAR FLOW, HYPERSONIC CHARACTERISTICS, CONICAL BODIES, SLENDER BODIES, GUIDED MISSILE MODELS, REYNOLDS NUMBER, SHOCK WAVES, MACH NUMBER, MODEL TESTS, ANGLE OF ATTACK, BASE FLOW, BASE PRESSURE

Subject Categories : Aerodynamics
      Guided Missile Dynam, Config & Cntrl Surfaces
      Unmanned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE