NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
An experimental investigation of nacelle-pylon installation on an unswept wing at subsonic and transonic speedsA wind tunnel investigation was conducted to determine the aerodynamic interference associated with the installation of a long duct, flow-through nacelle on a straight unswept untapered supercritical wing. Experimental data was obtained for the verification of computational prediction techniques. The model was tested in the 16-Foot Transonic Tunnel at Mach numbers from 0.20 to 0.875 and at angles of attack from about 0 deg to 5 deg. The results of the investigation show that strong viscous and compressibility effects are present at the transonic Mach numbers. Numerical comparisons show that linear theory is adequate for subsonic Mach number flow prediction, but is inadequate for prediction of the extreme flow conditions that exist at the transonic Mach numbers.
Document ID
19840010094
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Carlson, J. R. (NASA Langley Research Center Hampton, VA, United States)
Compton, W. B., III (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2246
NASA-TP-2246
L-15589
Accession Number
84N18162
Funding Number(s)
PROJECT: RTOP 505-43-43-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available