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Overview of initial research into the effects of strong vortex flow on hybrid rocket combustion and performanceAn examination of the effect of vortex flow on hybrid rocket combustion and performance is underway. Emphasis is on response of the fuel regression rate when subjected to vortex flow. Initial results show that there is a definite effect of the vortex on fuel regression rate. Future work will focus on quantitatively measuring this regression rate. This work is part of an overall program to develop an ultra low cost fuel system for hybrid rocket engines.
Document ID
19960009787
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gloyer, P.
(Tennessee Univ. - Calspan Tullahoma, TN, United States)
Knuth, William H.
(Tennessee Univ. - Calspan Tullahoma, TN, United States)
Goodman, J.
(Tennessee Univ. - Calspan Tullahoma, TN, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1993
Publication Information
Publication: Center for Space Transportation and Applied Research Fifth Annual Technical Symposium Proceedings
Subject Category
Spacecraft Propulsion And Power
Accession Number
96N16953
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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