NDLI: Integration effects of underwing forward- and rearward-mounted separate-flow, flow-through nacelles on a high-wing transport

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Integration effects of underwing forward- and rearward-mounted separate-flow, flow-through nacelles on a high-wing transport

Content Provider	NASA Technical Reports Server (NTRS)
Author	Lamb, M. Abeyounis, W. K.
Copyright Year	1986
Description	An experimental investigation was conducted in the Langley 16-Foot Transonic Tunnel at free-stream Mach numbers from 0.70 to 0.82 and angles of attack from -2.5 to 4.0 degrees to determine the integration effects of pylon-mounted underwing forward and rearward separate-flow, flow-through nacelles on a high-wing transonic transport configuration. The results showed that the installed drag of the nacelle/pylon in the rearward location was slightly less than that of the nacelle/pylon in the forward location. This reduction was due to the reduction in calculated skin friction of the nacelle/pylon configuration. In all cases the combined value of form, wave, and interference drag was excessively high. However, the configuration with the nacelle/pylon in a rearward location produced an increase in lift over that of the basic wing-body configuration.
File Size	2013906
Page Count	36
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19860012043
Archival Resource Key	ark:/13960/t9q28sv1q
Language	English
Publisher Date	1986-04-01
Access Restriction	Open
Subject Keyword	Aerodynamics Aerodynamic Drag Body-wing Configurations Skin Friction Transonic Wind Tunnels Flow Distribution Wind Tunnel Tests Nacelles Pylons Mach Number Loads Forces System Effectiveness Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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