Accession Number:

AD0818398

Title:

A STUDY OF LARGE, HIGH-PERFORMANCE SHOCK TUNNEL DRIVERS.

Descriptive Note:

Interim rept. Feb-May 67,

Corporate Author:

AVCO MISSILES SPACE AND ELECTRONICS GROUP WILMINGTON MA AVCO SPACE SYSTEMS DI V

Report Date:

1967-07-17

Pagination or Media Count:

100.0

Abstract:

A study has been performed to determine the optimum, practical high-energy driver technique to be employed with the Air Force Aero Propulsion Laboratory 120-inch shock tunnel. The aerodynamic performance and engineering design and feasibility of several candidate techniques have been investigated. An internally and statically heated, 6-inch ID driver tube, employing hydrogen at a maximum pressure of 30,000 psi and a maximum temperature of 1000 F is recommended as the optimum, practical system. Such a driver will provide true speed, pressure, and temperature simulation along the corridor. Moreover, the engineering design of the heater, seals, diaphragm, and safety system are all within the current state-of-the-art, while the problem of hydrogen embrittlement of the driver tube appears solvable.

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE