Boundary Layer Separation in 2 and 3 Dimensional High Speed Blow.
Abstract
Laminar boundary flow on cones in supersonic flow was calculated using a modified Method of Integrals to account for the change in velocity profiles in the separated regions. The work was extended to three dimensions and compared to experimental data. Significant progress was made in the modeling of th flows and in particular the regions of separated and reverse flow in the boundary layer.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1987
- Accession Number
- ADA181301
Entities
People
- Maurice Holt
Organizations
- University of California, Berkeley