Experimental and Numerical Analysis of the Aerodynamic and Aeroacoustic Properties of a 2D High-LiftWing Model

Aerodynamic and acoustic measurements of a 2D high-lift wing-section in flap full span deployed and flap side-edge (half span deployed) configurations are investigated both experimentally and numerically to understand the acoustic noise characteristics and the mechanisms of noise generation presented both in the slat and flap side-edge. Experimental analysis is carried out at the LAE-1 closed test section wind-tunnel and measured data includes phased array beamforming results along with steady pressure and hot-film anemometry measurements while numerical analysis using the PowerFLOW® software intends to replicate wind-tunnel conditions with hard-wall boundaries and results from both aerodynamic unsteadiness and far field predictions are presented. The high-lift model is a 2D wing model with single slotted flaps and slats. Tests were conducted both in full deployed flap or in half stowed configuration, for flap side-edge noise analysis. Results provide also comparisons between numerical and experimental data for steady aerodynamic data regarding surface pressure and flap side-edge vortex measurements along with unsteady aerodynamic measurements taken from hot-film anemometry performed at the slat in both chordwise and spanwise directions and far field acoustic noise predictions.