Accession Number : AD0868288

Title :   On the Hypersonic Flow Past Blunted, Flat Delta Wings,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Polak, Arnold

Report Date : 05 JAN 1970

Pagination or Media Count : 23

Abstract : The flow of a perfect gas over the slab portion of a blunted delta wing flying at hypersonic speeds is studied. A set of approximate equations is derived and a solution - for an inviscid flow - is obtained. Using this solution as a representation for the inviscid flow problem, a formulation to the laminar boundary-layer equations is presented; one which is applicable to the flow field's azimuthal planes where the crossflow gradients are not too large. Numerical solutions to these boundary-layer equations have been obtained; however, these are restricted to the azimuthal planes and near to the leading edges. The results indicate the presence of a dividing surface streamline since a numerical solution could not be obtained near the centerplane of the wing, where the crossflow velocity is large. (Author)

Descriptors :   (*DELTA WINGS, HYPERSONIC CHARACTERISTICS), BLUNT BODIES, CONICAL BODIES, LEADING EDGES, BOUNDARY LAYER, NUMERICAL ANALYSIS, EQUATIONS OF MOTION.

Subject Categories : Guided Missiles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE