Using hypothesis that low frequency oscillations (chugging) in rocket engines, are result of oscillatory propellant flow induced by combustion time lag, conditions for suppression of such oscillations are derived; stability can be achieved by increases in length of feed line, velocity of propellant in feed line, ratio of feed pressure to chamber pressure, and ratio of chamber volume to nozzle area.
Theory of unstable combustion in liquid propellant rocket systems
Am Rocket Soc -- J
American Rocket Society -- Journal ; 21 , n 5
1951
7 pages
Article (Journal)
English
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Liquid propellant rocket combustion instability
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