Viscous Flow Over a Cone at Moderate Incidence. II. Supersonic Boundary Layer,
Abstract
A numerical finite difference method recently developed to study three-dimensional viscous flow is applied here to the supersonic flow over a sharp cone at moderate angles of incidence (a/0 < 2, a=angle of attack, 0=cone half angle). In a previous analysis, the hypersonic merged and strong interaction regions were considered. In this paper the supersonic boundary layer farther downstream is evaluated. The system of governing equations incorporates lateral diffusion and centrifugal force effects; and an improved numerical scheme has been developed. Detailed flow structure including surface heart transfer, boundary layer profiles and thickness, and the formation of swirling pairwise symmetric vortices, associated with crossflow separation are obtained.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1972
- Accession Number
- AD0755862
Entities
People
- S. G. Rubin
- T. C. Lin
Organizations
- New York University Tandon School of Engineering