NDLI: Space storable propellant performance gas/liquid like-doublet injector characterization

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Space storable propellant performance gas/liquid like-doublet injector characterization

Content Provider	NASA Technical Reports Server (NTRS)
Author	Falk, A. Y.
Copyright Year	1972
Description	A 30-month applied research program was conducted, encompassing an analytical, design, and experimental effort to relate injector design parameters to simultaneous attainment of high performance and component (injector/thrust chamber) compatibility for gas/liquid space-storable propellants. The gas/liquid propellant combination selected for study was FLOX (82.6% F2)/ambient temperature gaseous methane. The injector pattern characterized was the like-(self)-impinging doublet. Program effort was apportioned into four basic technical tasks: injector and thrust chamber design, injector and thrust chamber fabrication, performance evaluation testing, and data evaluation and reporting. Analytical parametric combustion analyses and cold flow distribution and atomization experiments were conducted with injector segment models to support design of injector/thrust chamber combinations for hot fire evaluation. Hot fire tests were conducted to: (1) optimize performance of the injector core elements, and (2) provide design criteria for the outer zone elements so that injector/thrust chamber compatibility could be achieved with only minimal performance losses.
File Size	114974153
Page Count	191
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19720026080
Archival Resource Key	ark:/13960/t1gj48430
Language	English
Publisher Date	1972-10-01
Access Restriction	Open
Subject Keyword	Propellants Methane Injectors Liquid Rocket Propellants Thrust Chambers Storable Propellants Flox Gaseous Rocket Propellants Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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