Abstract
The computational model of a jet-wing configuration from the recent TsAGI experiment [1] that corresponds to a dual-stream co-axial subsonic jet under a swept lifting wing is considered. For the jet and wing calculations, Monotonically Integrated Large Eddy Simulations (MILES) are performed for which a modern parallel unstructured-grid computational code based on the high-resolution CABARET scheme [2],[3] is used. The computational domain includes the co-axial nozzle with a central body and a lifting wing section where round flowstoppers were installed on the wing tips to prevent downwash effects. For far-field noise predictions, the MILES CABARET solver is coupled with the Ffowcs Williams – Hawkings (FW-H) integral method. The FW-H solution corresponds to a large closed permeable control surface with multiple closing disks at the outlet side in accordance with the best practice. The results of the acoustic modelling are compared with the experiment. The differences, which can be associated with the unaccounted effects of sound refraction through a non-uniform free-stream flow are discussed.
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