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.
Computations of Transonic, Chemically Reacting Flows in Rocket Nozzles
1983
15 pages
Report
Keine Angabe
Englisch
Numerical Study of Chemically Reacting Flow in Nozzles
NTIS | 1989
|A numerical study of chemically reacting flow in nozzles
NTRS | 1989
|