Ejector Effects on a Supersonic Nozzle at Low Altitude and Mach Number
Abstract
This research involves the study of ejector effects on a supersonic nozzle. A blowdown wind tunnel was used to simulate the launch of an ejector rocket to determine possible thrust augmentation capabilities of such a design. Pressure measurements were made along the mixing chamber during the 42 separate runs which were used to select a specified profile to study the effects the flow has on wall pressures and rocket thrust. Primary airflow was directed to the primary rocket nozzle designed for Mach 3.09. Secondary airflow was directed to a sonic ejector which was adjusted to simulate vehicle Mach number. A vacuum tank was used to provide the environment simulating a reverse trajectory of a launch. Theses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1988
- Accession Number
- ADA206049
Entities
People
- Christopher A. Seaver
Organizations
- Air Force Institute of Technology