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Intergration effects of D-shaped, underwing, aft-mounted, separate-flow, flow-through nacelles on a high-wing transportAn experimental investigation was conducted in the Langley 16-Foot Transonic Tunnel at freestream Mach numbers from 0.70 to 0.82 and angles of attack from -3.0 to 4.0 deg to determine the integration effects of D-shaped, underwing, aft-mounted, separate-flow, flow-through nacelles on a high-wing transonic transport configuration. The results showed that the aft-mounted nacelle/pylon produced an increase in lift over that of the wing-body configuration by pressurizing much of the wing lower surface in front of the pylon. For the D-shaped nacelle, a substantial region of supersonic flow over the wing, aft of the lip of the nacelle, cancelled the reduction in drag caused by the increase in pressures ahead of the lip, to increase interference and form drag compared with a similar circular-shaped nacelle. The installed drag of the D=shaped nacelle was essentially the same as that of an aft-mounted circular nacelle from a previous investigation.
Document ID
19880001391
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Lamb, Milton (NASA Langley Research Center Hampton, VA, United States)
Carlson, John R. (NASA Langley Research Center Hampton, VA, United States)
Pendergraft, Odis C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
November 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-4018
L-16342
NAS 1.15:4018
Accession Number
88N10773
Funding Number(s)
PROJECT: RTOP 505-68-91-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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