C. Balan and J.W. AskewGeneral Electric Aircraft Engines, Cincinnati, Ohio

Static Aerodynamic Performance Investigationof a Fluid Shield Nozzle

NASA/CR—2005-213321

January 2005

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C. Balan and J.W. AskewGeneral Electric Aircraft Engines, Cincinnati, Ohio

Static Aerodynamic Performance Investigationof a Fluid Shield Nozzle

NASA/CR—2005-213321

January 2005

National Aeronautics andSpace Administration

Glenn Research Center

Prepared under Contract NAS3–25951

Available from

NASA Center for Aerospace Information7121 Standard DriveHanover, MD 21076

National Technical Information Service5285 Port Royal RoadSpringfield, VA 22100

Available electronically at http://gltrs.grc.nasa.gov

Document History

This research was originally published internally as HSR027 in May 1996.

Note that at the time of writing, the NASA Lewis Research Centerwas undergoing a name change to the

NASA John H. Glenn Research Center at Lewis Field.Both names may appear in this report.

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NASA CR—2005-213321

E–14781

WBS–22–714–09–46NAS3–25951

Static Aerodynamic Performance Investigation of a Fluid Shield Nozzle

C. Balan and J.W. Askew

Unclassified -UnlimitedSubject Categories: 01, 05, and 07 Distribution: Nonstandard

General Electric Aircraft EnginesOne Neumann WayCincinnati, Ohio 45125

This research was originally published internally as HSR027 in May 1996. Responsible person, Diane Chapman, Ultra-Efficient Engine Technology Program Office, NASA Glenn Research Center, organization code PA, 216–433–2309.

In pursuit of an acoustically acceptable, high performance exhaust system capable of meeting Federal Aviation

Regulation 36—Stage 3 noise goals for the High Speed Civil Transport application, General Electric Aircraft Engines

conducted a design study to incorporate a fluid shield into a 36-chute suppressor exhaust-nozzle system. After a full

scale preliminary mechanical design of the resulting fluid shield exhaust system, scale model aerodynamic perfor-

mance tests and acoustic tests were conducted to establish both aerodynamic performance and acoustic characteristics.

Data are presented as thrust coefficients, discharge coefficients, chute-base pressure drags, and plug static pressure

distributions.

High speed civil transport; Fluid shield; Exhaust-nozzle system72