Three-Dimensional, Two-Phase, Transonic, Canted Nozzle Flows
Abstract
A time-dependent numerical scheme, in conjunction with a three- dimensional, body-fitted coordinate transformation technique, is used for the solution of subsonic-transonic-supersonic flows: both gas-only, one-phase and fully coupled, gas-particle, two-phase flows inside three-dimensional canted nozzles of arbitrary configurations. The emphasis of the study is placed upon the transonic flow solution, which has been a bottleneck in many three- dimensional nozzle flow studies. Precise interpretation of flow variables in a canted nozzle is obtained through the simultaneous solution of multiple flow regions for motor aft closure and nozzle with two different coordinate centerlines. Numerical calculations are carried out for the seven-segment Titan IV solid rocket motor aft closure and nozzle internal flow field. The results of the three-dimensional flow analysis are in good agreement with available test data, and constitute the first rigorous numerical solution for canted nozzle flows since the inception of the Titan solid rocket motor program more than 25 years ago.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 02, 1988
- Accession Number
- ADA211528
Entities
People
- I-shih Chang
Organizations
- The Aerospace Corporation