NASA Logo

NTRS - NASA Technical Reports Server

Back to Results
Wind Tunnel Investigation of Passive Porosity Applied to the Leading-Edge Extension and Leading-Edge Flaps on a Slender Wing at Subsonic SpeedA wind tunnel experiment was conducted in the NASA Langley Research Center 7- by 10-Foot High Speed Tunnel to determine the effects of passive surface porosity on the subsonic vortex flow interactions about a general research fighter configuration. Flow-through porosity was applied to the leading-edge extension, or LEX, and leading-edge flaps mounted to a 65deg cropped delta wing model as a potential vortex flow control technique at high angles of attack. All combinations of porous and nonporous LEX and flaps were investigated. Wing upper surface static pressure distributions and six-component forces and moments were obtained at a free-stream Mach number of 0.20 corresponding to a Reynolds number of 1.35(106) per foot, angles of attack up to 45deg, angles of sideslip of 0deg and +/-5deg, and leading-edge flap deflections of 0deg and 30deg.
Document ID
20170004505
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Erickson, Gary E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
May 9, 2017
Publication Date
March 1, 2017
Subject Category
Aerodynamics
Report/Patent Number
NF1676L-26349
NASA-TM-2017-219596
L-20784
Report Number: NF1676L-26349
Report Number: NASA-TM-2017-219596
Report Number: L-20784
Funding Number(s)
WBS: WBS 147016.03.07.04.02
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