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
Personal Author(s) : Smith, C. E. ; Hajjar, D. G. ; Reinecke, W. G.
Report Date : 17 JUL 1967
Pagination or Media Count : 100
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.
Descriptors : (*SHOCK TUBES, PERFORMANCE(ENGINEERING)), SHOCK(MECHANICS), UNDERGROUND STRUCTURES, SUPERSONIC COMBUSTION, SUPERSONIC COMBUSTION RAMJET ENGINES, AERODYNAMICS, HELIUM, HYDROGEN, SIMULATION, VELOCITY, HYDROSTATIC PRESSURE, HEATERS, O RINGS, DIAPHRAGMS(MECHANICS).
Subject Categories : Test Facilities, Equipment and Methods
Distribution Statement : APPROVED FOR PUBLIC RELEASE