LBM-based Direct Noise Computation of a Swept High-Lift Wing Section with Slat-Track and Active Noise Control

This work focuses on the Direct Noise Computation (DNC) of high-lift wing sections using the wall-modelled LES (WM-LES) Lattice Boltzmann Method (LBM). The research code ProLB is used as a solver here. This study is formulated as a continuation of our previously published work that involved a systematic validation of the numerical DLR/ONERA F16 high-lift wing, without sweep, against the experimental results. For this investigation, the complexity of the F16 wing is augmented by adding a sweep component and a slat-track in an incremental fashion. Initially, the slat-track geometry used in predecessor projects is investigated. Upon comparing with the outcome of the no slat-track case, it was verified that the presence of a track in the slat cove increases the overall noise. To negate this additional noise, a reduction measure is thought of in the form of a local flow control in the vicinity of the track. This is realized by steadily blowing bleed air at the track to push away the oncoming free-stream flow to go around the track. In other words, creating an air curtain to deflect the flow away from the track. To inspect this local flow control measure, the air is steadily blown sequentially along the streamwise (X-axis, parallel to the track) and the spanwise direction (Z-axis, perpendicular to the track).In this work, we discuss the efficacy of the steady blowing concept and of an alternative passive measure i.e. porous material to reduce the extra noise induced by the presence of a slat track in the slat cove.