Experimental Results of Laminar Boundary Layer Separation on a Slender Cone at Angle of Attack at M infinity equals 14.2
Abstract
Wind tunnel experiments with a 5.6 degree half angle cone at M infinity = 14.2 indicated that the three-dimensional separation bubble concept was not the correct flow field model for these data. Based on data consisting of surface pressure measurements, pitot pressure surveys, and surface oil flow patterns, a new model for hypersonic three dimensional separation is proposed. This model contains symmetrical supersonic helical vortices with an attachment line on the most leeward ray. The vortices are in contact with the surface (at least up to alpha = 18 degrees) and there is no subsonic reverse flow or singular points associated with the vortex pattern.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1971
- Accession Number
- AD1214091
Entities
People
- Kenneth F. Stetson