Accession Number : AD0655076

Title :   HYPERSONIC VISCOUS FLOW OVER SLENDER BODIES HAVING SHARP LEADING EDGES,

Corporate Author : POLYTECHNIC INST OF BROOKLYN N Y DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS

Personal Author(s) : Rudman,Stanley ; Rubin,Stanley G.

Report Date : MAY 1967

Pagination or Media Count : 85

Abstract : The hypersonic viscous pressure interaction is treated by the development of a set of equations valid throughout the boundary layer, shock-wave structure and inviscid core. Primary interest is concerned with the nature of the leading edge continuum merged layer in which the shock wave and boundary layer are indistinguishable. Due to the parabolic nature of the equations, finite-difference solutions are attainable. The flow over a flat plate at zero incidence, as well as angle of attack, was considered. Velocity and state variable distributions across the viscous layer depict the formation of an outer shock wave and inner constant pressure boundary layer. The calculated values of surface pressure, heat transfer and shock jump conditions were at first significantly below the values predicted by strong interaction theory. Agreement was quite good downstream of the merged layer where Rankine-Hugoniot jump conditions were satisfied to within 8%. (Author)

Descriptors :   (*HYPERSONIC FLOW, *SLENDER BODIES), LEADING EDGES, BOUNDARY LAYER, SHOCK WAVES, FLAT PLATE MODELS, ANGLE OF ATTACK, INTERACTIONS, MATHEMATICAL ANALYSIS

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE