Oil Flow Studies of Base Separation at Supersonic Speeds.
Abstract
Oil flow visualization tests were conducted on the base of a 10-degree half-angle cone model at Mach numbers 1.75 to 4.0. The cone was supported by a strut from the cone surface to the wind tunnel floor. Previous tests on a sting supported cone showed separation to occur on the cone base at distances on the order of 15% of the base radius from the trailing edge corner. Results of this test program show that separation occurs at slightly greater distances from the corner than for the sting supported model; also, the separation line was irregular indicating large asymmetries in the base flow even though the model was at zero degrees attitude. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1975
- Accession Number
- ADA014981
Entities
People
- Lyle D. Kayser
Organizations
- Ballistic Research Laboratory