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Test Capability Enhancements to the NASA Langley 8-Foot High Temperature TunnelThe NASA Langley 8-Foot High Temperature Tunnel produces true enthalpy environments simulating flight from Mach 4 to Mach 7, primarily for airbreathing propulsion and aerothermal/thermo-structural testing. Flow conditions are achieved through a methane-air heater and nozzles producing aerodynamic Mach numbers of 4, 5 or 7 and have exit diameters of 8 feet or 4.5 feet. The 12-ft long free-jet test section, housed inside a 26-ft vacuum sphere, accommodates large test articles. Recently, the facility underwent significant upgrades to support hydrocarbon fueled scramjet engine testing and to expand flight simulation capability. The upgrades were required to meet engine system development and flight clearance verification requirements originally defined by the joint NASA-Air Force X-43C Hypersonic Flight Demonstrator Project and now the Air Force X-51A Program. Enhancements to the 8-Ft. HTT were made in four areas: 1) hydrocarbon fuel delivery; 2) flight simulation capability; 3) controls and communication; and 4) data acquisition/processing. The upgrades include the addition of systems to supply ethylene and liquid JP-7 to test articles; a Mach 5 nozzle with dynamic pressure simulation capability up to 3200 psf, the addition of a real-time model angle-of-attack system; a new programmable logic controller sub-system to improve process controls and communication with model controls; the addition of MIL-STD-1553B and high speed data acquisition systems and a classified data processing environment. These additions represent a significant increase to the already unique test capability and flexibility of the facility, and complement the existing array of test support hardware such as a model injection system, radiant heaters, six-component force measurement system, and optical flow field visualization hardware. The new systems support complex test programs that require sophisticated test sequences and precise management of process fluids. Furthermore, the new systems, such as the real-time angle of attack system and the new programmable logic controller enhance the test efficiency of the facility. The motivation for the upgrades and the expanded capabilities is described here.
Document ID
20070003589
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Harvin, S. F.
(NASA Langley Research Center Hampton, VA, United States)
Cabell, K. F.
(NASA Langley Research Center Hampton, VA, United States)
Gallimore, S. D.
(Swales Aerospace Hampton, VA, United States)
Mekkes, G. L.
(Jacobs Sverdrup Technology, Inc. Hampton, VA, United States)
Date Acquired
August 24, 2013
Publication Date
January 1, 2006
Subject Category
Research And Support Facilities (Air)
Meeting Information
Meeting: JANNAF 41st Combustion/29th Airbreathing Propulsion/23rd Propulsion Systems Hazards Joint Subcommittee Meeting
Location: San Diego, Ca
Country: United States
Start Date: December 4, 2006
End Date: December 8, 2006
Sponsors: Department of the Army, Department of the Navy, NASA Headquarters, Department of the Air Force
Funding Number(s)
WBS: WBS 759-07-06
Distribution Limits
Public
Copyright
Public Use Permitted.
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