Airframe/Propulsion Integration at Transonic Speeds

[+] Author and Article Information
W. P. Henderson

Applied Aerodynamics Division, NASA Langley Research Center, Hampton, VA 23665

J. Eng. Gas Turbines Power 113(1), 51-59 (Jan 01, 1991) (9 pages) doi:10.1115/1.2906530 History: Received January 22, 1990; Online April 24, 2008


A significant level of research is ongoing at NASA’s Langley Research center on integrating the propulsion system with the aircraft. This program has included nacelle/pylon/wing integration for turbofan transports, propeller/nacelle/wing integration for turboprop transports, and nozzle/afterbody/empennage integration for high-performance aircraft. The studies included in this paper focus more specifically on pylon shaping and nacelle bypass ratio studies for turbofan transports, nacelle and wing contouring, and propeller location effects for turboprop transports, empennage effects, and thrust vectoring for high-performance aircraft. The studies were primarily conducted in NASA Langley’s 16-Foot Transonic Tunnel at Mach numbers up to 1.20.

Copyright © 1991 by The American Society of Mechanical Engineers
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