Analysis of liquid rocket propellant in nitroglycerin injector reactors
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The Present Status of Propellant Feed Pumps for Liquid Rockets
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Overview of Combustion Instabilities in Liquid-Propellant Rocket Engines [PDF]
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Culick, Fred E. C., Yang, Vigor
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An Experimental and Analytical Study of High-Energy-Density Propellants for Liquid Rocket Engines
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Further studies of liquid sloshing in rocket propellant tanks Final report, 25 Mar. 1961 - 31 Dec. 1965 [PDF]
Liquid sloshing and dynamics in rocket propellant tanks annotated bibliography with ...
Abramson, H. N.
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Performance Prediction of Liquid Rocket Thrust Chambers with Nonuniform Propellant Mixing
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A study of high frequency nonlinear combustion instability in baffled annular liquid propellant rocket motors. Volume 2 - A user manual for computer programs TRDL and TRDPLT Final report, 25 Aug. 1969 - 25 Sep. 1970 [PDF]
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Burstein, S. Z., Schechter, H. S.
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, 1968 A high number of liquid oxygen and gaseous hydrogen orifices per unit area are provided in an injector head designed to give intimate mixing and more thorough combustion.
Green, C. W., Jr.
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A Reliable Method for Predicting the Specific Impulse of Chemical Propellants
Journal of Aerospace Technology and Management, 2018 The specific impulse (Isp) is an important performance parameter that describes energy efficiency of propellant combustion and is intimately related to the rocket engine thrust.
Dany Frem
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