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The NASA Langley Scramjet Test ComplexThe NASA Langley Scramjet Test Complex consists of five propulsion facilities which cover a wide spectrum of supersonic combustion ramjet (scramjet) test capabilities. These facilities permit observation of the effects on scramjet performance of speed and dynamic pressure from Mach 3.5 to near-orbital speeds, engine size from Mach 4 to 7, and test gas composition from Mach 4 to 7. In the Mach 3.5 to 8 speed range, the complex includes a direct-connect combustor test facility, two small-scale complete engine test facilities, and a large-scale complete engine test facility. In the hypervelocity speed range, a shock-expansion tube is used for combustor tests from Mach 12 to Mach 17+. This facility has recently been operated in a tunnel mode, to explore the possibility of semi-free-jet testing of complete engine modules at hypervelocity conditions. This paper presents a description of the current configurations and capabilities of the facilities of the NASA Langley Scramjet Test Complex, reviews the most recent scramjet tests in the facilities, and discusses comparative engine tests designed to gain information about ground facility effects on scramjet performance.
Document ID
19960044656
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
R.W. Guy
(Langley Research Center Hampton, Virginia, United States)
R.C. Rogers
(Langley Research Center Hampton, Virginia, United States)
R.L. Puster
(Langley Research Center Hampton, Virginia, United States)
K. E. Rock
(Langley Research Center Hampton, Virginia, United States)
G. S. Diskin
(Langley Research Center Hampton, Virginia, United States)
Date Acquired
August 17, 2013
Publication Date
July 1, 1996
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
NASA-TM-111658
AIAA Paper 96-3243
NAS 1.15:111658
Meeting Information
Meeting: 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Location: Lake Buena Vista, FL
Country: US
Start Date: July 1, 1996
End Date: July 3, 1996
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
96N72462
Distribution Limits
Public
Copyright
Public Use Permitted.
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