An Experimental Study of Clustered Nozzles with Variable Shrouds.
Abstract
The research of this thesis involved the investigation of pressure and flow fields in the base region of clustered nozzles during cold flow testing. Nozzle exit conditions simulating altitudes up to 75,000 feet and chamber-to-back pressure ratios up to 200 were used. The nozzle clusters considered were made up of sets of two and three dimensional supersonic convergent-dirvergent nozzles with a square shroud around the cluster. The two dimensional nozzles had design exit Mach numbers of 3.68 and 2.94. The three dimensional nozzles had a design exit Mach number of 2.64. The nozzle clusters were studied using various configurations and with two shroud lengths. A schlieren system that allowed for both still photographs and motion pictures film was used to investigate the flow fields. The results of this study indicate that the pressure fields in the base region of a nozzle cluster are dependent on both geometry and on the operating altitude. The outer wall of the test section (shroud) adjacent to the nozzles was observed to significantly affect the flow patterns and measured pressures. Potential influences in performance exist due both to changes in the gas dynamics of the flow and the appearance of additional pressure-area forces.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1985
- Accession Number
- ADA163961
Entities
People
- James R. Moran
Organizations
- Air Force Institute of Technology