Year: 2024
Type: article
Abstract: The paper presents the results of wing noise simulations for the prototype of supersonic business jet in landing mode. The near-field airflow is modeled according to Delayed Detached Eddy Simulation approach. The finite-volume vertex-centered scheme with the low weight of upwind component is used for convective flux approximation. The noise at the far-field points is calculated by the Ffowcs Williams–Hawkings method. The noise spectra at the near-field points are presented, and the impact of local mesh resolution and numerical instability on the near-field acoustics is discussed. For the Ffowcs Williams–Hawkings method due to the features of the wing geometry and the resulting flow configuration, we used non-standard integration surfaces to reduce computational costs of the scale-resolving simulations. Additionally, we employed optimized mesh resolution on the integration surfaces to significantly reduce the dick space required for storing the data for far-field noise calculations. The tests performed for the near-field and far-field points demonstrated applicability of the proposed optimizations.
Authors: Alexey P. Duben, Tatiana K. Kozubskaya, Pavel V. Rodionov
Institution: Keldysh Institute of Applied Mathematics
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: diamond
Awards: G597338630, G6444257319
OpenAlex ID: W4403777021