Accession Number : AD0637614

Title :   SUPERSONIC INTERFERENCE FLOW ALONG THE CORNER OF INTERSECTING WEDGES.

Corporate Author : RAND CORP SANTA MONICA CALIF

Personal Author(s) : Charwat,A. F. ; Redekopp,L. G.

Report Date : JUL 1966

Pagination or Media Count : 56

Abstract : An experimental investigation of the inviscid supersonic flow field in a corner formed by two intersecting wedges is reported. The study includes measurements of the distribution of the surface pressure and the wave structure of the flow field in the corner region both for a symmetrical corner configuration (e. e., equal wedge angles) in the Mach-number range between 2.5 and 4 and for an asymmetrical model at one Mach number as a function of the incidence angle of one wedge. A clearly identifiable shock structure is discovered that divides the interference field into four zones. The total extent of the disturbance near the surfaces of the model is approximately twice the extent indicated by available small-perturbation analyses. The highest pressure rise occurs in the inner zone near the corner; the magnitude of this rise is related successfully to the second-order linearized theory. The inviscid flow field is shown to involve strong cross-stream pressure and entropy gradients both at the corner proper and away from it, which cannot be disregarded in analyses of the viscous boundary layer. (Author)

Descriptors :   (*RAREFIED GAS DYNAMICS, *WEDGES), SUPERSONIC FLOW, HYPERSONIC FLOW, AERODYNAMIC CONFIGURATIONS, WINGS

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE