This 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.
Flowfield measurements about a multi-element airfoil at high Reynolds numbers
AIAA, Fluid Dynamics Conference ; 1993 ; Orlando, FL, United States
1993-07-01
Conference paper
No indication
English
FULL-LENGTH PAPERS - High Reynolds Number, Multielement Airfoil Flowfield Measurements
Online Contents | 2000
|Supercritical Airfoil Flowfield Measurements
AIAA | 1975
|