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Subsonic Investigation of a Leading-Edge Boundary Layer Control Suction System on a High-Speed Civil Transport ConfigurationA wind tunnel investigation of a leading edge boundary layer control system was conducted on a High Speed Civil Transport (HSCT) configuration in the Langley 14- by 22-Foot Subsonic Tunnel. Data were obtained over a Mach number range of 0.08 to 0.27, with corresponding chord Reynolds numbers of 1.79 x 10(exp 6) to 5.76 x 10(exp 6). Variations in the amount of suction, as well as the size and location of the suction area, were tested with outboard leading edge flaps deflected 0 and 30 deg and trailing-edge flaps deflected 0 and 20 deg. The longitudinal and lateral aerodynamic data are presented without analysis. A complete tabulated data listing is also presented herein.
Document ID
20000023177
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Campbell, Bryan A. (NASA Langley Research Center Hampton, VA United States)
Applin, Zachary T. (NASA Langley Research Center Hampton, VA United States)
Kemmerly, Guy T. (NASA Langley Research Center Hampton, VA United States)
Coe, Paul L., Jr. (NASA Langley Research Center Hampton, VA United States)
Owens, D. Bruce (NASA Langley Research Center Hampton, VA United States)
Gile, Brenda E. (NASA Langley Research Center Hampton, VA United States)
Parikh, Pradip G. (Boeing Co. Seattle, WA United States)
Smith, Don (Boeing Co. Seattle, WA United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 1999
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-1999-209700
L-17917
NAS 1.15:209700
Funding Number(s)
PROJECT: RTOP 537-03-22-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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