Shock Detachment from the Leading Edge of Delta Wings.
Abstract
Angles of attack for shock wave detachment from the sharp leading edge of five delta wing models with flat compression surfaces were determined experimentally and the results are compared with analytical prediction methods. The wind tunnel experiments were performed at a free stream Mach number of 14.2 and a free stream Reynolds number per foot of 62,000. The angle of attack for shock wave detachment was experimentally determined by observing the flow of oil from the compression side of the model around the leading edge. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1972
- Accession Number
- AD0752206
Entities
People
- Kenneth F. Stetson
- Norman E. Scaggs
Organizations
- Air Force Research Laboratory