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.


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    A numerical study of chemically reacting flow in nozzles

    Vanoverbeke, Thomas J. / Shuen, Jian-Shuen | NTRS | 1989


    A numerical study of chemically reacting flow in nozzles

    VANOVERBEKE, THOMAS / SHUEN, JIAN-SHUN | AIAA | 1989


    A numerical study of chemically reacting flow in nozzles

    Vanoverbeke, Thomas J. / Shuen, Jian-Shun | NTRS | 1989