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

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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

Author(s):
Wright, Robert Kincaid
Author Organization(s):
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO
Supplementary Note:
Master's thesis.
Annotation:
The performance of a convergentdivergent nozzle in a shock tube.
Pagination:
0107

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFIT-GAE/ME/63 12
Monitor Series:
GAE/ME/63 12
 Subject Terms
Communities of Interest:
Air Platforms
Descriptor(s):
*CONVERGENT DIVERGENT NOZZLES, SHOCK TUBES, OSCILLOSCOPES, HELIUM, FLUIDS
Report Date:
1963 Aug 01