某舰飞行甲板区域流场特性的水洞试验

Water Tunnel Experiment of the Flowfield in the Warship Flight Deck

为了满足舰载直升机的需要，南航直升机技术研究所对某舰飞行甲板区域流场进行了水洞试验。本文详述了水洞试验的方法和技术，通过对舰模在各种水速、各种航行偏角状态下的试验，得到了大量照片，并据此对该舰机库后部、飞行甲板上部周围流场进行了分析，得出了在飞行甲板机库门外有一趋于收缩的稳态区，随着流速Ｖ的增大，这一区域变短。稳态区之后很快变为乱流区。从侧面上看，稳态区高度有从降低再向上扩散的趋向。在向右偏航时，左侧收缩较右侧稍大。在β＝０（°）时机库门的开和关对流场的影响不大。当β＞４５（°）后，乱流区扩大到有少许进入机库门内，而当机库门关闭，乱流区由于受到门的阻挡，扩散并翻卷到机库上方。

An experiment of the flowfield in the warship flight deck area is carried out in the water tunnel for different flow velocities and navigation direction angles. The method used for the experiment is discribed and the flowfield pictures is analyzed, by which a steady zone out of the door of the helicopter hangar is found. This steady zone has a tendency of contraction as the flow velocity increasing, and it will disappear when the flow velocity is higher than a value. There is a turbulent area just behind the steady zone. This area diffuseing at it rear part and its front edge goes up to the helicopter hangar as the velocity increases. When the water flows sideward, the flow contracts more. No obvious effect on the flow pattern whether the door is opened or closed. When β >45(°), however, the flowfield almost has no contraction, and the turbulent area extends into the hangar (if the door is open) or rolled up (if the door is close).