The Effects of a Morphed Trailing-Edge Flap on the Aeroacoustic and Aerodynamic Performance of a 30P30N Aerofoil

This paper presents initial results on the aeroacoustic and aerodynamic effects of morphing trailing-edge flap 30P30N aerofoil, over five deflections (5–25°), at an 8° angle attack a Reynolds number Re=9.2×105. The Ffowcs-Williams–Hawkings acoustic analogy estimates far-field noise, whilst flow field is solved using URANS with four-equation Transition SST model. Aerodynamic simulation data for 30P30N’s full configuration compare well experimental results. A Courant (C) ≤ 1 should be used resolving tonal C up to 4 sufficient broadband noise. Sound pressure level show average 11% reduction in noise across all frequencies morphed compared conventional, single-slotted flap. eliminates multiple peaks observed conventional design. Beyond 15° deflection, achieves higher stall angles, but increased drag, leading maximum 17% Cl/Cd ratio methodology reported here quick tool performance design stage.