Computation of Aerodynamic and Acoustic Characteristics of NACA0012 Airfoil Using the Zonal RANS–IDDES Approach
- Авторы: Shorstov V.1, Makarov V.1
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Учреждения:
- Central Institute of Aviation Motors
- Выпуск: Том 11, № 1 (2019)
- Страницы: 9-21
- Раздел: Article
- URL: https://journals.rcsi.science/2070-0482/article/view/202858
- DOI: https://doi.org/10.1134/S2070048219010150
- ID: 202858
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Аннотация
The presented results of computations of the aerodynamic and acoustic characteristics of an isolated symmetric NACA0012 airfoil with a blunt trailing edge in a subsonic homogeneous viscous perfect gas flow at zero angle of attack are obtained using the MP5 modified finite-difference scheme proposed in this study. The computations are accomplished within the zonal RANS–IDDES approach engaging the basic RANS Spalart–Allmaras model. A synthetic turbulence generator with a three-dimensional source is used to create turbulent content at the entrance to the IDDES domain. A series of model problems are considered, whose solutions allowed tuning the parameters of the proposed difference scheme and solving some methodological problems related to processing the simulation results.
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Об авторах
V. Shorstov
Central Institute of Aviation Motors
Email: vmakarov@ciam.ru
Россия, Moscow
V. Makarov
Central Institute of Aviation Motors
Автор, ответственный за переписку.
Email: vmakarov@ciam.ru
Россия, Moscow