Flows in the Annular Region when an Underexpanded Nozzle is Exhausted into a Stepped Launch Tube.
Abstract
An experimental program has been conducted in which unheated air was exhausted through a stationary rocket nozzle into a constant-area-tube launcher modified with a constrictive ring. The constrictive ring simulates a constraint which could be a permanent or temporary part of the launch tube. For the first phase of the test program the static wall-pressure distribution, upstream and downstream of the ring, and the mass flow-rates in the annular gap were measured. Given an underexpanded nozzle, a correlation between the generation blow-by, or reverse flow in the annular gap, and the position of the nozzle exit-plane relative to the front face of the ring was developed. The flow phenomena present in the launcher for different nozzle positions has also been investigated. For the second phase of the test program the static pressure distribution on the surface of the rocket and the mass flow-rates in the annular gap were measured. The differential pressure distributions on the rocket were related to the mass flow-rate in the annular gap with increasing blow-by flow, and with increasing ejector flow. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1980
- Accession Number
- ADA088581
Entities
People
- John J. Bertin
- Stanley A. Bouslog
Organizations
- University of Texas at Austin