公开(公告)号：US5884871A

公开(公告)日：1999-03-23

申请号：US827403

申请日：1997-03-27

申请人： Alexander V. Fedorov ,  Norman D. Malmuth

发明人： Alexander V. Fedorov ,  Norman D. Malmuth

IPC分类号： B64C23/00 ,  B64C30/00 ,  B64C21/00

CPC分类号： B64C23/00 ,  B64C30/00 ,  B64C2230/14 ,  B64C2230/20 ,  B64C2230/22 ,  Y02T50/166

摘要： A method is provided for hypersonic laminar flow control which uses the effect of boundary layer stabilization by an ultrasonically transparent coating. A hypersonic body surface is covered by the coating which absorbs the flow disturbance energy and does not trip the boundary layer flow. In one embodiment, the coating is made from a porous material of regular structure containing cylindrical blind microholes normal to the body surface. In another embodiment, the porous material has random distributions of pore shape and orientation. Extraction of the flow disturbance energy by pores causes stabilization of the boundary layer on the coated surface and leads to laminar-turbulent transition delay. The method can be used to decrease the aerodynamic drag of hypersonic vehicles and reduce heat transfer on vehicle surfaces.

摘要翻译： 提供了一种用于超音速层流控制的方法，其使用通过超声波透明涂层进行边界层稳定的效果。 超音速的身体表面被涂层覆盖，吸收流动扰动能量，不会跳动边界层流动。 在一个实施方案中，涂层由具有垂直于体表的圆柱形盲孔的规则结构的多孔材料制成。 在另一个实施方案中，多孔材料具有孔形状和取向的随机分布。 通过孔提取流动扰动能导致涂层表面上边界层的稳定化，并导致层流湍流转变延迟。 该方法可用于降低超音速车辆的空气动力学阻力并减少车辆表面的热传递。