Published February 1, 1959 | Version Submitted
Technical Report Open

Operation and Performance of a Shock Tube with Heated Driver

Abstract

A shock tube was constructed with a driver section which could be heated with "Calrod" heaters to temperatures of approximately 300°C. This temperature rise increased the shock wave Mach number by about 40 per cent, or from values of 7.7 to 10 for pressure ratios of 2O,000 across the diaphragm. This increase is sufficient to produce partial dissociation of the oxygen molecules behind the shock wave. The flow behind the shock wave was as uniform as that produced by an unheated driver. A transition section was designed to enable the major portion of the low pressure chamber to be constructed of round Shelby tubing, while the test section still had a flat top and a flat bottom. The flat surfaces are advantageous for optical studies and for convenience in instrumenting the tube. Despite the fact that the transition was gradual, disturbances were present in the flow in the test section, 18 inches downstream of the transition section.

Additional Information

Hypersonic Research Project Memorandum No. 48. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.

Attached Files

Submitted - No._48.pdf

Files

No._48.pdf

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Additional details

Identifiers

Eprint ID
61719
Resolver ID
CaltechAUTHORS:20151029-151142532

Funding

U.S. Army Office of Ordnance
DA-04-495-Ord-19

Dates

Created
2015-10-29
Created from EPrint's datestamp field
Updated
2019-10-03
Created from EPrint's last_modified field

Caltech Custom Metadata

Caltech groups
Hypersonic Research Project
Series Name
Hypersonic Research Project Memorandum
Series Volume or Issue Number
48