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Flowfield measurements about a multi-element airfoil at high Reynolds numbersThis paper describes experimental data obtained with a multi-element airfoil at flight Reynolds numbers and lift coefficients including Clmax. The wind tunnel test was conducted in the NASA Langley Low Turbulence Pressure Tunnel as part of a cooperative effort between McDonnell Douglas Aerospace and NASA Langley. The airfoil model is a supercritical design configured with a leading-edge slat and a single-segment trailing-edge flap. Data include surface static-pressure distributions (integrated to obtain lift), drag data obtained with wake-rake surveys, and fbwfield surveys obtained with a flat-tube and five-hole probe at nine stations on the configuration's upper surface. Effects of variations in Reynolds number and flap gap on airfoil performance and flowfield survey data are presented.
Document ID
19930064303
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chin, Vincent D.
(NASA Langley Research Center Hampton, VA, United States)
Peters, David W.
(McDonnell Douglas Aerospace Long Beach, CA, United States)
Spaid, Frank W.
(McDonnell Douglas Aerospace Saint Louis, MO, United States)
Mcghee, Robert J.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-3137
Meeting Information
Meeting: AIAA, Fluid Dynamics Conference
Location: Orlando, FL
Country: United States
Start Date: July 6, 1993
End Date: July 9, 1993
Sponsors: AIAA
Accession Number
93A48300
Distribution Limits
Public
Copyright
Other

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