Book Description

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 performance 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.Balan, C. and Askew, J. W.Glenn Research CenterCIVIL AVIATION; EXHAUST NOZZLES; AERODYNAMIC CHARACTERISTICS; AIRCRAFT ENGINES; MECHANICAL ENGINEERING; SHIELDING; FLUID FLOW; STATIC PRESSURE; DATA REDUCTION; THRUST; PLUGS; PRESSURE DISTRIBUTION; NOZZLE FLOW; NOISE REDUCTION