Computation of Aerodynamic and Acoustic Characteristics of NACA0012 Airfoil Using the Zonal RANS–IDDES Approach
- Авторлар: Shorstov V.1, Makarov V.1
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Мекемелер:
- Central Institute of Aviation Motors
- Шығарылым: Том 11, № 1 (2019)
- Беттер: 9-21
- Бөлім: Article
- URL: https://journals.rcsi.science/2070-0482/article/view/202858
- DOI: https://doi.org/10.1134/S2070048219010150
- ID: 202858
Дәйексөз келтіру
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.
Негізгі сөздер
Авторлар туралы
V. Shorstov
Central Institute of Aviation Motors
Email: vmakarov@ciam.ru
Ресей, Moscow
V. Makarov
Central Institute of Aviation Motors
Хат алмасуға жауапты Автор.
Email: vmakarov@ciam.ru
Ресей, Moscow