The analysis of secondary flows for tube-launched rocket configurations
Abstract
Theoretical flow-fields have been calculated for various nozzle/launch-tube configurations using this flow model. The solutions, thus calculated, are compared with experimental data in the present paper. The principal objectives of the present paper are (1) to present and engineering model for the impingement flow-field which is produced when an underexpanded supersonic nozzle is exhausted into constant-area tube, (2) to compare the computed flow-field solutions with experimental results, and (3) to use the comparisons to establish the validity of the flow model.
- Publication:
-
Final Report
- Pub Date:
- January 1981
- Bibcode:
- 1981tua..rept.....K
- Keywords:
-
- Aerodynamic Configurations;
- Flow Distribution;
- Numerical Analysis;
- Rocket Launchers;
- Secondary Flow;
- Supersonic Nozzles;
- Fluid Flow;
- Jet Mixing Flow;
- Mass Flow;
- Pipes (Tubes);
- Shock Waves;
- Fluid Mechanics and Heat Transfer