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On the Supersonic Flow over an Axisymmetric Step at an Angle of Attackстатья
Информация о цитировании статьи получена из
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Scopus
Статья опубликована в журнале из списка Web of Science и/или Scopus
Дата последнего поиска статьи во внешних источниках: 12 января 2022 г.
- Авторы: Simonenko M.M., Guvernyuk S.V., Kuzmin A.G.
- Журнал: AIP Conference Proceedings
- Том: 2027
- Номер: 030023 (2018)
- Год издания: 2018
- Первая страница: 1
- Последняя страница: 9
- DOI: 10.1063/1.5065117
- Аннотация: The work addresses 3D supersonic flow over a stepped axisymmetric body with a nose cone. Dependencies of flow regimes on the angle of attack α and length L of the body part ahead of the step are studied. Experiments were conducted in the A-7 wind tunnel of the Research Institute of Mechanics, Moscow State University, at a free-stream Mach number of 3. The study reveals bands of the angle α and length L in which flow pressure on the leeward side of step increases with increasing α or L, and eventually it exceeds the pressure on the windward side. Numerical simulations are performed with a finite-volume solver on the basis of URANS equations. The supersonic flow structure at a given length L and angles of attack from 0 to 16° is scrutinized. The simulations unveil a supersonic jet propagating along the bodyleeward side. The jet is located between a pair of side vortices formed due to a development of the transversal flow separation. At α>5° and sufficiently large L, the supersonic jet impact creates a spot of anomalously high pressure on the leeward side of the step.
- Добавил в систему: Симоненко Михаил Михайлович
Прикрепленные файлы
| № | Имя | Описание | Имя файла | Размер | Добавлен |
|---|---|---|---|---|---|
| 1. | Полный текст | 1.5065117.pdf | 1,8 МБ | 6 ноября 2018 [mmsimon] |