On the Hypersonic Flow Past Blunted, Flat Delta Wings,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 05, 1970
- Accession Number
- AD0868288
Entities
People
- Arnold Polak
Organizations
- Naval Ordnance Laboratory