http://swrc.ontoware.org/ontology#UnrefereedArticle
Computation of Two-Dimensional, Transonic, Chemically Reacting Nonequilibrium Flow in a Rocket Nozzle
en
NAKAHASHI Kazuhiro
宇宙科学研究所
Institute of Space and Astronautical Science
The Institute of Space and Astronautical Science report. S.P. : Proceedings of the Symposium on Mechanics for Space Flight
1
51-64
1983-03
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.
0288-433X
AA10455137
資料番号: SA0033404000