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Integration effects of pylon geometry on a high-wing transport airplaneAn investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the installation effects of a series of pylons that had differing cross-sectional shapes on the pressure distributions and aerodynamic characteristics of a 1/24-scale high wing transport. The tests were conducted at Mach numbers at 0.70 and 0.80 at angles of attack from -3 degrees to 4 degrees with the pylons tested at various toe angles between 5 degrees inboard and 5 degrees outboard. Results of this study indicate that the installed drag was lowest for the pylons with a compression pylon type design which kept the flow under the wing in the pylon/wing junction comparable to the clean wing velocities.
Document ID
19890006517
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Carlson, John R. (NASA Langley Research Center Hampton, VA, United States)
Lamb, Milton (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-2877
L-16489
NAS 1.60:2877
Accession Number
89N15888
Funding Number(s)
PROJECT: RTOP 535-03-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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