Laminar-turbulent transition on the flying wing model

被引：6

作者：

Pavlenko, A. M. ^{[1
]}

Zanin, B. Yu. ^{[1
]}

Katasonov, M. M. ^{[1
]}

机构：

[1] Khristianovich Inst Theoret & Appl Mech SB RAS, Novosibirsk, Russia

来源：

INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2016) | 2016年 / 1770卷

关键词：

D O I：

10.1063/1.4964002

中图分类号：

O59 [应用物理学];

学科分类号：

摘要：

Results of an experimental study of a subsonic flow past aircraft model having "flying wing" form and belonging to the category of small-unmanned aerial vehicles are reported. Quantitative data about the structure of the flow near the model surface were obtained by hot-wire measurements. It was shown, that with the wing sweep angle 34 the laminar-turbulent transition scenario is identical to the one on a straight wing. The transition occurs through the development of a package of unstable oscillations in the boundary layer separation.

引用

页数：7