Low-Speed Wind Tunnel Tests on a Lambda Wing High-Lift Configuration

Abstract

A test of a slotted high -lift system on a military wing of novel planform was conducted in the Defense Evaluation and Research Agency (DERA) 5 -Metre wind tunnel (now QinetiQ 5 -Metre wind tunnel). The testing was conducted under the auspices of The Technical Co -operation Program (TTCP), a multi -national research collaboration program involving the United Kingdom Defense Evaluation and Research Agency , the United States Department of Navy, NASA, an d the United States Department of the Air Force. The prime objectives were to understand the basic flow physics of military slotted high -lift configurations on wings having novel planforms , optimize the rigging (height and overhang) of the slotted trailin g edge flap system, and validate computational fluid dynamics (CFD) codes. Three shroud settings and two trailing edge flap angles were evaluated over a range of trailing edge flap height and overhang conditions on a semi - span wing/body configuration. Fo rce and moment, surface pressure, and surface flow visualization data were acquired. The results show the dependence of flap height and overhang, trailing edge flap angle, shroud angle, Reynolds number, and Mach number on aerodynamic performance.