Cold Aero Performance of a Two-Dimensional Mixer Ejector Nozzle
Cold Aero Performance of a Two-Dimensional Mixer Ejector Nozzle by C. Balan, published by BiblioLife in July 2013, presents a detailed examination of the cold aerodynamic performance of a two-dimensional mixer-ejector (2DME) exhaust system. This edition, comprising 130 pages, is written in English and explores the critical elements of environmental acceptability and economic viability in the development of a second-generation supersonic civil transport, known as High Speed Civil Transport (HSCT). The book outlines the significance of meeting strict airport noise regulations and the role of innovative propulsion systems in achieving these standards.
Readers will find a comprehensive analysis of the test program conducted by GE Aircraft Engines at the NASA Langley 16 ft transonic wind tunnel. The study investigates various factors affecting the performance of the 2DME exhaust system, including suppressor area ratio, overall exhaust system exit area, flap length, and free stream Mach number. This work contributes to the broader discourse on aerospace engineering, particularly in the context of politics and government, as it addresses the intersection of technological advancement and regulatory compliance in the aviation industry.
Official synopsis Publisher
Since 1986, NASA and the U.S. aerospace industry have been assessing the economic viability and environmental acceptability of a second-generation supersonic civil transport, or High Speed Civil Transport (HSCT). Environmental acceptability in terms of airport community noise and economic viability are critical elements in this endeavor. Development of a propulsion system that satisfies strict airport noise regulations (FAR36 Stage III levels), at acceptable performance and weight, is critical to the success of any HSCT program. Two-dimensional mixer-ejector (2DME) exhaust systems are one approach in achieving this goal. In support of HSCT development, GEAE (GE Aircraft Engines), under contract to the NASA Glenn Research Center, conducted this test program at the NASA Langley 16 ft transonic wind tunnel to evaluate the cold aerodynamic performance aspects of the 2DME exhaust system concept. The effects of SAR (SAR, suppressor area ratio, = mixed-flow area/primary nozzle throat area), MAR (MAR = overall exhaust system exit/mixing-plane area), flap length, CER (suppressor chute expansion ratio), chute alignment, and free stream Mach number were investigated on a 1/11th cold aerodynamic scale model of a 2DME exhaust system.
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