Flow field produced by rocket exhaust impingement on a multi-tube launcher
Abstract
An experimental program has been conducted in which simulated underexpanded exhaust plumes impinge on the face of a multi-tube launcher. The test variables included: distance from the nozzle exit-plane to the launcher assembly, stagnation pressure of the simulated rocket, and number of open tubes. Supercritical flows were obtained in which a large fraction of the exhaust gas spread over the face of the launcher assembly with attendant high pressures. The most important parameter in defining the impingement flow field was the ratio of plume-diameter/tube-diameter.
- Publication:
-
American Institute of Aeronautics and Astronautics Conference
- Pub Date:
- June 1982
- Bibcode:
- 1982aiaa.confS....B
- Keywords:
-
- Exhaust Flow Simulation;
- Flow Distribution;
- Jet Impingement;
- Rocket Exhaust;
- Rocket Launchers;
- Supersonic Jet Flow;
- Convergent-Divergent Nozzles;
- Diameters;
- Flow Geometry;
- Inviscid Flow;
- Pipe Flow;
- Pressure Distribution;
- Stagnation Pressure;
- Supercritical Flow;
- Viscous Flow;
- Fluid Mechanics and Heat Transfer