Experimental characterization of the spray originating from an impinging-jet injector in a liquid-rocket engine

Author:

Lourme D.,Schmitt D.,Brault F.

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference21 articles.

1. Les moyens nécessaires à l'étude fondamentale des instabilités de combustion d'un moteur biliquide;Lourme;Acta Astronautica,1983

2. Dropsize distribution for impinging-jet breakup in air-streams simulating the velocity conditions in rocket combustors;Ingebo;NACA TN-4222,1958

3. Maximum stable droplets in dispersoids;Mugele;AIChE. J.,1960

4. Correlation of spray injector parameters with rocket engine performance;Dickerson;AFRPL-TL-68-147,1968

5. L. J. Zajac, Correlation of spray dropsize distribution and injector variables. NASA-CR-125674.

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1. Experimental Investigation of a LOX Spray under Hot Fire Conditions;Proceedings of the Seventh International Conference on Liquid Atomization and Spray Systems;2023

2. Experimental investigation of atomization characteristics of swirling spray by ADN gelled propellant;Acta Astronautica;2018-03

3. HOLOGRAPHIC INVESTIGATION OF THE EFFECT OF ELEVATED AMBIENT TEMPERATURE ON THE ATOMIZATION CHARACTERISTICS OF IMPINGING JET SPRAYS;Atomization and Sprays;1997

4. Combustion Instability Analysis: Numerical Analysis of Engine Instability;Liquid Rocket Engine Combustion Instability;1995-01-01

5. Impinging jets atomization;Physics of Fluids A: Fluid Dynamics;1991-12

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