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Preliminary wind-tunnel investigation of the effects of engine nacelles on a transport configuration with high lift drag ratios to a Mach number of 1.00Wind tunnel tests to determine the effect of engine nacelles added to a low wing fuselage vertical tail configuration utilizing the NASA supercritical airfoil and a refined area ruled fuselage are discussed. The engine arrangement consisted of two aft fuselage, side mounted flow through nacelles and a solid body of revolution mounted above the fuselage in a manner similar to the Boeing 727. A preliminary analysis of the wind tunnel data shows that favorable interference drag can be obtained with the proper longitudinal locations of the nacelles, by canting the nacelle inlets, and by cusping the rearward region of the nacelle.
Document ID
19810010573
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Flechner, S. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
February 16, 1971
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
LWP-939
NASA-TM-82312
Accession Number
81N19099
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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