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Compression PylonA compression pylon for an aircraft with a wing-mounted engine, that does not cause supersonic airflow to occur within the fuselage-wing-pylon-nacelle channel is presented. The chord length of the pylon is greater than the local chord length of the wing to which it is attached. The maximum thickness of the pylon occurs at a point corresponding to the local trailing edge of the wing. As a result, the airflow through the channel never reaches supersonic velocities.
Document ID
19900010762
Acquisition Source
Headquarters
Document Type
Other - Patent
Authors
Patterson, James C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
September 19, 1989
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
Patent Number: US-PATENT-4,867,394
Patent Application Number: US-PATENT-APPL-SN-210480
Patent Number: NASA-CASE-LAR-13777-1
Accession Number
90N20078
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,867,394|NASA-CASE-LAR-13777-1
Patent Application
US-PATENT-APPL-SN-210480

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