Accession Number:

ADA094735

Title:

Flow Characteristics in a Channel Following Exit of Incident Shock Wave.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1980-12-01

Pagination or Media Count:

50.0

Abstract:

Dynamic variations in pressure occurring within shock tube channels following the exit of an incident shock wave were investigated. Three channel sizes were investigated. The first size was 4 in by 8 by 48 in 10.16 cm by 20.32 cm by 1.22 m, the second size was 4 in by 1 in by 25 in 10.16 cm by 2.54 cm by 63.5 cm, and the third size was 1 in by 1 in by 44 in 2.54 cm by 2.54 cm by 1.12 m. For the first and second channels, the shock tube diaphragm pressure ratio, P sub 41 ranged from 6.0 to 20.0. The third channel was used over a P sub 41 range of 8.0 to 20.0 and also to determine the presence of transverse waves due to an area reduction in the shock tube. The first channel, having the same cross-sectional area as the shock tube, exhibited pressures which approximated simple shock tube theory results. The second and third channels exhibited complex pressure changes which consistently peaked at the same time after the shock wave passed the pressure sensors, independent of P sub 41.

Subject Categories:

  • Lasers and Masers
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE