The space station uses small rocket motors, called thrusters, for orientation control. Because of the lack of viable design tools for small rockets, the initial thruster design was basically a very small version of a large rocket motor. Thrust measurements of the initial design were lower than predicted. To improve predictions it was decided to develop a verison of the RPLUS2D reacting flow code for thruster calculations. RPLUS2D employs an implicit finite volume, lower-upper symmetric successive overrelaxation (LU-SSOR) scheme for solving the complete two-dimensional Navier-Stokes equations and species transport equations in a coupled and very efficient manner. The combustion processes are modeled by a 9-species, 18 step finite-rate chemistry model, and the turbulence is simulated by a Baldwin-Lomax algebraic model. The code is extended to handle multiple subsonic inlet conditions where the total mass flow is governed by conditions calculated at the thruster-throat. Results are shown for a thruster design where the overall mixture ratio is hydrogen rich. A calculation of a large area ratio divergent nozzle is also presented.
Numerical Study of Chemically Reacting Flow in Nozzles
1989
21 pages
Report
No indication
English
Rocket Engines & Motors , Combustion & Ignition , Fluid Mechanics , Convergent-divergent nozzles , Flow distribution , Reaction kinetics , Rocket engines , Two dimensional models , Computer programs , Thrust measurement , Chemical reactions , Computational fluid dynamics , Inlet flow , Navier-stokes equation , Nozzle geometry , Pressure effects , Propellant combustion , Temperature effects , Turbulence models , Viscosity
A numerical study of chemically reacting flow in nozzles
AIAA | 1989
|A numerical study of chemically reacting flow in nozzles
NTRS | 1989
|A numerical study of chemically reacting flow in nozzles
NTRS | 1989
|