Open AccessTheoretical Analysis of Supersonic Low Reynolds Number Flow Control Technique Based on Flow Mixing
Author(s) -
Xu Dachuan,
Zhaohui Ren,
Zhiqiang Chen,
Haifeng Wang,
Long-de Guo
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/751/1/012009
Subject(s) - boundary layer , mechanics , reynolds number , supersonic speed , hele shaw flow , flow separation , flow (mathematics) , choked flow , boundary layer thickness , isothermal flow , external flow , open channel flow , boundary layer control , shock wave , physics , materials science , turbulence
The thickness of boundary layer increases rapidly in supersonic low Reynolds number flows. As a result, there will be shock wave-boundary layer interference. The disturbances of downstream can spread upstream through in boundary layer because the flow in boundary layer is subsonic, which may decrease flow field uniformity and stability. The pressure of this type of flow is always very low. For the sake of flow continuity, the increase of flow pressure is necessary. A kind of supersonic low Reynolds number flow control technique was proposed. The high pressure supersonic flow jet-ted from plates which located in the flow channel blew away boundary layer, cut off the disturbances spread from downstream to upstream, and eliminated the shock wave-boundary layer interference. The pressure of primary flow was also increased by mixing with the high pressure jetting flow. The calculation model of this flow control technique was established. A group of standard inputs were selected to calculate the parameters of flow and the preliminary law of flow was also obtained.