Accession Number:

AD0868288

Title:

On the Hypersonic Flow Past Blunted, Flat Delta Wings,

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s):

Report Date:

1970-01-05

Pagination or Media Count:

23.0

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 fields 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

Subject Categories:

  • Guided Missiles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE