Computation of Two-Dimensional, Transonic, Chemically Reacting Nonequilibrium Flow in a Rocket Nozzle

概要

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A time-dependent, semi-implicit scheme is developed for solving the equations governing two-dimensional, chemically reacting nonequilibrium flow inside rocket nozzles. Subsonic and transonic flowfields of the nozzle entrance and throat region can be analyzed using this computational scheme. All equations of motion are solved simultaneously at each grid point by treating the time derivatives implicitly, in order to make the scheme stable with respect to the chemical rates. By evaluating spatial derivative terms explicitly, the scheme is made simple and has the advantage that only a relatively small computer storage is required. Results are presented at first for a nonreacting flow inside the JPL nozzle in order to illustrate the proposed scheme's validity by comparing with the experimental data and the result of the Cline's scheme. Then the nozzle flowfield of a hydrogen-oxygen rocket engine is analyzed. A computational result of C-H-O-N system (nitrogen tetroxide and a blend of 50 percent hydrazine and 50 percent unsymmetrical dimethylhydrazine) is also presented.
宇宙航空研究開発機構の論文