SST Technology Follow-On Program - Phase 2. Noise Suppressor/Nozzle Development. Volume 5. Advanced Suppressor Concepts and Full Scale Tests
Abstract
The goal of this program was to develop and demonstrate an engine exhaust system suitable for use on a commercial supersonic transport which would allow the airplane to meet FAR Part 36 takeoff and sideline noise requirements. A series of model-scale jet noise suppressor test programs and a design feasibility study were conducted to identify the exhaust system design which would meet this goal. A model-scale test and a full-scale test of a boilerplate version of the final design were conducted statically to demonstrate thrust performance and noise suppression characteristics. Full-scale test results were limited to a jet velocity of 2300 fps due to engine operating limits, while model-scale results were extended beyond the design velocity of 2550 fps. The full-scale suppressor system test achieved 15.8 PNdB sideline jet noise reduction for 0.75% static gross thrust loss at v sub j = 2300 fps. Model-scale tests of the same system show that the jet noise suppression should increase to 16.8 PNdB at v sub j - 2550 fps. Forward flight effects during climb-out are predicted to degrade the suppressor performance to a value of 15 PNdB noise reduction for 7% net thrust loss. Consequently, it is shown that the application of such a suppressor system to the Boeing B2707-300 SST configuration would achieve FAR Part 36 sideline noise levels. Further, it is shown that such an installation would allow an approximately 7.5% increase in the airplane's maximum takeoff weight, thereby improving its economic and mission flexibility.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1975
- Accession Number
- ADB004737
Entities
People
- C. P. Wright
- C. R. Fullerton
- J. Atvars
- R. S. Armstrong
Organizations
- Boeing