Interacting Supersonic Turbulent Boundary Layers Over a Two-Dimensional Protuberance.
Abstract
The report presents a numerical study of attached interacting supersonic turbulent boundary layers over a two-dimensional protuberance. Results are presented in terms of surface pressure, heat transfer and skin-friction distributions. These results indicate a strong effect of the size of the protuberance, Mach number, but a weak effect of Reynolds number and the ratio of wall-to-recovery temperature. The peak heating rates from a set of test cases compare well to a semi-empirical prediction method. In contradistinction to the laminar case, the turbulent recovery zone downstream of the protuberance is very short. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 21, 1974
- Accession Number
- AD0780691
Entities
People
- Arnold Polak
Organizations
- Naval Ordnance Laboratory