SST Technology Follow-on Program - Phase I, Performance Evaluation of an SST Noise Suppressor Nozzle System. Volume 1. Suppressed Mode.
Abstract
Acoustic and thrust performance tests were conducted on a 61-tube suppressor nozzle/ejector system designed for possible SST application. Static tests were conducted at temperatures from ambient to 1500 F. The primary variables were the shape of the upstream primary flow duct, placement of nozzle structural reinforcement beams, ejector inlet shape, use of acoustic linings, and use of an auxiliary acoustic shield. Low-speed wind tunnel tests investigated the effects on performance of ejector inlet shape and location. The best acoustic performance was obtained with an acoustic lining in the ejector and an additional lined shield extending beyond the ejector. Best performance was obtained with a flush ejector inlet. The acoustic lining and shield had no significant effect on static performance. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 15, 1972
- Accession Number
- AD0900399
Entities
People
- C. D. Simcox
- D. B. Morden
- H. Y. Lu
- R. L. Benefiel
Organizations
- Boeing