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Effect of pylon cross-sectional geometries on propulsion integration for a low-wing transportAn experimental program was conducted in the Langley 16-Foot Transonic Tunnel to evaluate the performance effects of various types of pylons on a 1/17th-scale, low-wing transport model. The model wing was designed for cruise at a Mach number of 0.77 and a lift coefficient of 0.55. The pylons were tested at two wing semispan locations over a range of toe-in angles. The effects of toe-in angle were found to be minimal, but the variation in geometry had a more pronounced effect on the lift characteristics of the model. A pylon whose maximum thickness occurred at the wing trailing edge, known as a compression pylon, proved to be the best choice in terms of retaining the flow characteristics of the wing without pylons. Practical considerations such as structural viability may necessitate modification of the compression pylon concept in order to take advantage of its apparent benefits.
Document ID
19930018881
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Ingraldi, Anthony M. (NASA Langley Research Center Hampton, VA, United States)
Naik, Dinesh A. (Vigyan Research Associates, Inc. Hampton, VA., United States)
Pendergraft, Odis C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
L-17149
NASA-TP-3333
NAS 1.60:3333
Accession Number
93N28070
Funding Number(s)
PROJECT: RTOP 535-03-10-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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