Accession Number : AD0853069

Title :   The Interaction of a Moving Shock with the Convergent Section in a Shock Tube.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s) : Peters,Martin H.

Report Date : MAR 1969

Pagination or Media Count : 60

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)

Descriptors :   (*NOZZLE GAS FLOW, *SHOCK WAVES), INTERACTIONS, SHOCK TUBES, AIR, SUPERSONIC CHARACTERISTICS, TWO DIMENSIONAL FLOW, AERODYNAMIC CONFIGURATIONS, REFLECTION, VELOCITY, THESES

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE