Accession Number:

AD0900399

Title:

SST Technology Follow-on Program - Phase I, Performance Evaluation of an SST Noise Suppressor Nozzle System. Volume 1. Suppressed Mode.

Descriptive Note:

Final rept. on task 4,

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Personal Author(s):

• Lu, H. Y.
• Morden, D. B.
• Benefiel, R. L.
• Simcox, C. D.

Report Date:

1972-02-15

Pagination or Media Count:

511.0

Abstract:

Acoustic and thrust performance tests were conducted on a 61-tube suppressor nozzleejector 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

Descriptors:

• *ACOUSTIC INSULATION
• *TURBOJET EXHAUST NOZZLES
• *JET ENGINE NOISE
• REDUCTION
• JET TRANSPORT AIRCRAFT
• THRUST AUGMENTATION
• SUPERSONIC NOZZLES
• DUCT INLETS
• CONVERGENT DIVERGENT NOZZLES
• SUBSONIC FLOW
• SUPERSONIC FLOW
• SUPPRESSORS
• TURBOJET INLETS
• BAFFLES
• JET PUMPS
• THRUST
• DRAG
• TEMPERATURE CONTROL
• WIND TUNNEL MODELS
• CAPTIVE TESTS
• PERFORMANCE(ENGINEERING)
• MICROPHONES
• LOW FREQUENCY
• VERY LOW FREQUENCY
• ULTRALOW FREQUENCY
• SUPERLOW FREQUENCY
• COMPUTER PROGRAMS
• DATA PROCESSING

Subject Categories:

• Transport Aircraft
• Acoustics
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE