The objective of the current work is to experimentally characterize the flowfield associated with an uni-element shear coaxial injector burning liquid oxygen/gaseous hydrogen (LOX/GH2) propellants. These experiments were carried out in an optically-accessible rocket chamber operating at a high pressure (approximately 400 psia). Quantitative measurements of drop size and velocity were obtained along with qualitative measurements of the disintegrating jet.
Flowfield Characterization in a LOX/GH2 Propellant Rocket
1993
31 pages
Report
No indication
English
Rocket Propellants , Rocket Engines & Motors , Fluid Mechanics , Characterization , Computational fluid dynamics , Flow distribution , Gaseous rocket propellants , Liquid rocket propellants , Thrust chambers , Hydrogen fuels , Liquid oxygen , Cryogenics , Drop size , High pressure , Velocity distribution
Flowfield characteristics in a liquid propellant rocket
NTRS | 1993
|Flowfield characteristics in a liquid propellant rocket
AIAA | 1993
|