Accession Number : AD0682294

Title :   BINARY BOUNDARY LAYERS ON SHARP CONES IN LOW DENSITY SUPERSONIC AND HYPERSONIC FLOW.

Descriptive Note : Final rept. Jun 67-Mar 68,

Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN

Personal Author(s) : Mayne,Arloe W. , Jr. ; Gilley,G. E. ; Lewis,Clark H.

Report Date : FEB 1969

Pagination or Media Count : 44

Abstract : The effects of surface mass transfer on the flow field around sharp slender cones at zero angle of attack in low density supersonic and hypersonic flow are computed using an iterative inviscid-viscous flow field calculation model. The perfect gas model which is developed considers nonsimilar binary gas boundary layers, viscous interaction, transverse curvature, wall slip, and temperature jump. The inviscid and viscous flow fields are matched using a displacement thickness that includes the effects of surface mass transfer, and the inviscid flow is computed using either the tangent cone theory or the conical shock expansion theory. Calculated effects of helium argon, carbon dioxide, and air injection on total drag values and surface pressure distributions are compared with experimental data. (Author)

Descriptors :   (*CONICAL BODIES, AERODYNAMIC CHARACTERISTICS), REYNOLDS NUMBER, SURFACE PROPERTIES, SLENDER BODIES, ANGLE OF ATTACK, SUPERSONIC CHARACTERISTICS, MATHEMATICAL MODELS, INTERACTIONS, DRAG, HYPERSONIC CHARACTERISTICS, BOUNDARY LAYER, PRESSURE, DISTRIBUTION, HELIUM, ARGON, CARBON DIOXIDE

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE