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A computational investigation of fuel mixing in a hypersonic scramjetA parabolized, Navier-Stokes code, SHIP3D, is used to numerically investigate the mixing between air injection and hydrogen injection from a swept ramp injector configuration into either a mainstream low-enthalpy flow or a hypervelocity test flow. The mixing comparisons between air and hydrogen injection reveal the importance of matching injectant-to-mainstream mass flow ratios. In flows with the same injectant-to-mainstream dynamic pressure ratio, the mixing definition was altered for the air injection cases. Comparisons of the computed results indicate that the air injection cases overestimate the mixing performance associated with hydrogen injection simulation. A lifting length parameter, to account for the time a fluid particle transverses through the mixing region, is defined and used to establish a connection of injectant mixing in hypervelocity flows, based on nonreactive, low-enthalpy flows.
Document ID
19930060233
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fathauer, Brett W.
(George Washington Univ. Hampton, VA, United States)
Rogers, R. C.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-2994
Meeting Information
Meeting: AIAA, Fluid Dynamics Conference
Location: Orlando, FL
Country: United States
Start Date: July 6, 1993
End Date: July 9, 1993
Sponsors: AIAA
Accession Number
93A44230
Distribution Limits
Public
Copyright
Other

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