Transition Induced by Distributed Roughness on Blunt Bodies in Supersonic Flow
Abstract
An empirical model has been developed that correlates transition due to distributed roughnesses, which range in height over five orders of magnitude. The data base is obtained from wind tunnels, arc heaters, and sounding rockets. The shapes included are hemispheres, biconics, and laminar stable. The correlation departs from previous attempts by dividing the body into two distinct regions: a forward region where concave streamline curvature dominates transition, and a following region where streamline curvature is not an influence. Noise is found to have little or no effect, and the extension of the correlation to roughnesses measured in microinches shows no observable smooth wall limit.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 29, 1976
- Accession Number
- ADA032009
Entities
People
- William M. Bishop
Organizations
- The Aerospace Corporation