The Interaction of a Moving Shock with the Convergent Section in a Shock Tube.
Abstract
Shock wave interaction with a region of decreasing area was investigated. A 4 in by 8 in air-air shock tube was used. Upstream Mach numbers ranged from 1.2 to 1.6. Configurations were a discontinuous decrease in area and the same discontinuous decrease in area followed by a convergent two-dimensional nozzle. The three nozzles used had convergence angles of 20, 30, and 37 degrees with nominal area ratio 25:1. Mach reflection occurred in all three nozzles. Velocity measurements of the two-dimensional shock were made using a shadowgraph system and time recording oscilloscope. Transmitted shock velocity was dependent on nozzle convergence angle. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1969
- Accession Number
- AD0853069
Entities
People
- Martin H. Peters
Organizations
- Air Force Institute of Technology