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NASA NTRS · 19670006401

Resonant combustion

Clayton, R. M.·Sotter, J. G.·Woodward, J. W.
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Abstract

Circumferential variations in resonant pressure wave, resonant combustion diagnostic techniques, and hydrodynamic response of injectors to high amplitude chamber pressure oscillations

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INJECTORCOMBUSTION PHYSICSPRESSURE WAVEROTATIONAL FLOW

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BibTeXRIS

Clayton, R. M., Sotter, J. G., Woodward, J. W.. 1966-10-31. Resonant combustion. https://ntrs.nasa.gov/citations/19670006401

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NASA NTRS1967

Liquid propulsion

The Resonant Combustion Program uses a bombing technique to precipitate the transition from the steady state to the resonant, or oscillatory, rocket combustion mode. The initial pressure disturbance produced by the high-explosive device, when exploded in a nonreactive environment of cold N2 gas, is a blast-wave having an initial amplitude of several thousand psi (within a radius of approximately one inch from the bomb case) which is still several hundred psi strong even at a radius of 4 to 5 in. The use of such a severe triggering disturbance has brought up the question of whether or not the violent sustained oscillatory mode observed in this program is forced by the character of the initial disturbance itself.

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