The Drag of Ridges of Finite Length in a Turbulent Boundary Layer (Soprotivlenie Otdel'nykh Nerovnostei Poverkhnosti v Turbulentnom Pogranichnom Sloe),
Abstract
The drag due to ridges of rectangular and rounded sections and finite length have been measured at Mach numbers of 0.73 and 2.52 using a skin-friction type balance mounted in the sidewall of a wind tunnel. Results are given for a single ridge and one mounted behind the other. The interference between two rectangular ridges is unfavourable at M = 0.73 but favourable at M = 2.52. For rounded ridges the drag is appreciably less and little interference is apparent for both Mach numbers. The drag of swept single ridges is shown to be proportional to cos squard alpha and cos cubed alpha for the rectangular and rounded sections respectively. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1975
- Accession Number
- ADA015659
Entities
People
- N. I. Nesterovich
- V. M. Kovalenko
Organizations
- Royal Aircraft Establishment