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Static Performance of Six Innovative Thrust Reverser Concepts for Subsonic Transport Applications: Summary of the NASA Langley Innovative Thrust Reverser Test ProgramThe NASA Langley Configuration Aerodynamics Branch has conducted an experimental investigation to study the static performance of innovative thrust reverser concepts applicable to high-bypass-ratio turbofan engines. Testing was conducted on a conventional separate-flow exhaust system configuration, a conventional cascade thrust reverser configuration, and six innovative thrust reverser configurations. The innovative thrust reverser configurations consisted of a cascade thrust reverser with porous fan-duct blocker, a blockerless thrust reverser, two core-mounted target thrust reversers, a multi-door crocodile thrust reverser, and a wing-mounted thrust reverser. Each of the innovative thrust reverser concepts offer potential weight savings and/or design simplifications over a conventional cascade thrust reverser design. Testing was conducted in the Jet-Exit Test Facility at NASA Langley Research Center using a 7.9%-scale exhaust system model with a fan-to-core bypass ratio of approximately 9.0. All tests were conducted with no external flow and cold, high-pressure air was used to simulate core and fan exhaust flows. Results show that the innovative thrust reverser concepts achieved thrust reverser performance levels which, when taking into account the potential for system simplification and reduced weight, may make them competitive with, or potentially more cost effective than current state-of-the-art thrust reverser systems.
Document ID
20000112934
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Asbury, Scott C.
(NASA Langley Research Center Hampton, VA United States)
Yetter, Jeffrey A.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
July 1, 2000
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2000-210300
L-17975
NAS 1.15:210300
Report Number: NASA/TM-2000-210300
Report Number: L-17975
Report Number: NAS 1.15:210300
Funding Number(s)
PROJECT: RTOP 522-25-31-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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