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Scramjet Engine Flowpath Development for the Hyper-X Mach 10 Flight TestThe third flight of the Hyper-X Research Vehicle at nearly Mach 10 in November 2004 demonstrated the potential for airbreathing propulsion at hypersonic speeds. The flowpath of the scramjet engine used in the Hyper-X Research Vehicle was developed using computational fluid dynamic based design method in combination with a systematic series of ground tests in the NASA HyPulse Shock Tunnel at conditions duplicating Mach 10 flight. The test model was a true scale height and length of the internal flight engine flowpath that was partial width and truncated fore and aft. Tests were conducted using a mixture of hydrogen augmented with two-percent silane. Silane gas served as an ignition aid during the short duration of the pulse facility tests. The engine inflow values of pressure, temperature, and Mach number were parametrically varied during the ground test entries to broaden the database over the expected uncertainty in the flight conditions. A review of the ground test technique and comparisons of the ground test pressures along with selected data from the third flight are presented.
Document ID
20050234608
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Rogers, R. C.
(NASA Langley Research Center Hampton, VA, United States)
Shih, A. T.
(NASA Langley Research Center Hampton, VA, United States)
Hass, N. E.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2005
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
ISABE-2005-1025
Report Number: ISABE-2005-1025
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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