Method is presented for using injector pattern design as basis for estimating gas composition and flow patterns in combustion zone of rocket engine; principles of gas-dynamics are applied to determine magnitude and direction of lateral flow in chamber as function of axial station; stream tube theory allows evaluation of chemical composition at any local area; from these data critical zones at chamber wall may be located and requirements for satisfactory protection determined; two examples and results of analysis are given.
Environmental effects upon rocket injector/chamber compatibility
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 12
1967
5 pages
Aufsatz (Zeitschrift)
Englisch
© Metadata Copyright Elsevier B. V. All rights reserved.
NTIS | 1966
|NTRS | 1968
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