Streamline Swallowing by Laminar Boundary Layers in Hypersonic Flow
Abstract
Flow over a cold-wall, 22.5-deg asymptotic half-angle hyperboloid at a free-stream Mach number of 10 and free-stream Reynolds numbers (based on nose radius) of 400, 4000, and 40,000 is considered. Numerical results from a streamline-swallowing, nonsimilar, laminar, boundary-layer analysis are compared with results from classical boundary-layer theory, second-order boundary-layer theory, and a fully viscous shock-layer analysis; the results of the latter are used as a standard of comparison. The major improvement effected by the streamline-swallowing analysis is the inclusion of shock curvature effects on the boundary conditions applied along the outer edge of the boundary layer. Results from the streamline-swallowing boundary-layer analysis agree better with the results of the fully viscous shock-layer analysis, than the classical boundary layer and the second-order boundary-layer results. Reasons for the success of one method and the failure of others are discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1971
- Accession Number
- AD0719748
Entities
People
- A. W. Mayne Jr.
- J. C. Adams Jr.
Organizations
- Arnold Engineering Development Complex