Flowfield measurements about a multi-element airfoil at high Reynolds numbers

TLDR

The airfoil model is a supercritical design featuring a leading‑edge slat and a single‑segment trailing‑edge flap. The study presents experimental data on a multi‑element supercritical airfoil at flight Reynolds numbers and lift coefficients up to Clmax. Experimental data were collected in the NASA Langley Low Turbulence Pressure Tunnel, measuring surface static pressure, wake‑rake drag, and flowfield using flat‑tube and five‑hole probes at nine upper‑surface stations. The results show how changes in Reynolds number and flap gap influence the airfoil’s performance and flowfield characteristics.

Abstract

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.