Time-Resolved 3D Simulation of an Aircraft Wing with Deployed High-Lift System

The turbulent flow around a high-lift configuration consisting of slat, main element and flap is simulated at a Reynolds number of 1.7 × 106 with an implicit finite-volume based numerical method. The 3D unsteady motion in separated flow regions is resolved on a 25 million volume mesh employing the recent Delayed Detached-Eddy Simulation (DDES) approach [12]. Compressible calculations and the use of non-reflecting boundary conditions enable sound radiation to be captured in the simulation. The presented results cover the first step in a two-step approach towards the prediction of noise emitted into the acoustic farfield and provide insight into the complex flow dynamics in the slat region. The computed pressure distributions, statistics and spectra exhibit good agreement with findings from NASA Langley Research Center (LaRC) [2, 5].

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