Accession Number:

AD0419597

Title:

THE PERFORMANCE OF A CONVERGENT-DIVERGENT NOZZLE IN A SHOCK TUBE,

Descriptive Note:

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1963-08-01

Pagination or Media Count:

107.0

Abstract:

An investigation was conducted to determine the performance of a Mach 4, converging-diverging, sharp-edge-throat nozzle modification to the Mechanical Engineering Department shock tube. Mach Number measurements were made in the exit plane of the nozzle with a two-dimensional wedge and flow field pictures were recorded using a folded Schlieren system and high-speed motion picture photography. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE