最后简单介绍了目前在研究湍流边界层分离方面的进展。
Finally recent studies of turbulent boundary layer separation are also briefly reviewed.
理论分析和实验的结果说明：边界层分离将引起压差阻力。
The theoretical analysis and experimental results show that boundary layer separation will produce pressure drag.
微型压力传感器阵列的引入，拓宽了边界层分离点检测的解决途径。
The introduction of micro pressure sensor array expands ways detecting boundary layer separation point.
通过对压力面边界层分离条件的分析得出叶片型线方程并给出计算实例。
According to the analysis on the boundary layer separation condition, parameter equation of vane curve for centrifugal pump is established.
建立任意廻转面叶片表面边界层基本方程组，分析边界层分离的旋转效应。
The basic equations of the boundary layer for blade surface flow of arbitrary cyclical surface are established, and the rotating effect for boundary layer separation is analyzed.
边界层分离点、物面最小压力点及阻力系数的计算结果与一些数值解及实验结果是符合的。
The boundary layer separation points, minimum pressure positions on the surface and the drag coefficients are in agreement with numerical solutions and experimental results.
微型剪应力传感器以尺寸小、时空分辨率高的特点在边界层分离点测量中表现出了突出的优势。
Micro-shear stress sensor plays an important role in detecting separation point of the boundary layer due to small-scale structures and the desired spatial and temporal resolution.
本文就以用于实现三角翼边界层分离点检测的面向灵巧蒙皮的微型剪应力传感器为对象展开研究。
The micro shear stress sensor which based on the smart skin for boundary-layer separation point detection of delta wing has been explored in this paper.
设计的微型压力传感器阵列可有效满足边界层分离点的检测要求，进一步拓展了MEMS器件的工程应用范围。
This design proposal of micro pressure sensor array can effectively meeting the measuring requirement of boundary - layer separation point, and expand engineering applied scope of MEMS devices.
适宜采用微型涡流发生器对超临界翼型边界层分离进行控制，其最佳位置应在分离线前2~5H涡流发生器高度之间。
The experimental results also show that the optimum effective position range was found to be 2H to 5H of micro vortex generator height upstream of baseline separation.
在重力式油水分离场中，剪切流场主要存在于各种聚结填料中和器壁的流动边界层内。
In the gravity type oil water separating field, the shearing field mainly exists in all kinds of collison packing and flow boundary of vessel.
若分离参考点接近于出口端，则可获得满意的测试结果，这说明边界层实际分离点的位置已经很接近于叶片的出口端。
If the reference separation point approaches the outlet, the test results are satisfactory, which state that the practical position of boundary layer separation point will be close to the outlet.
在大气层某一定的高度以上，火箭后体上的边界层将会由于羽流引起分离。
Above some altitude within atmosphere layer, the boundary layer on after body will separate due to plume.
实验证明通过改变叶片型线参数方程中的速度系数的取值，可以控制边界层的分离，进而改善泵的性能，提高其水力效率。
The experiment shows that by changing the velocity coefficient , the separation of boundary layer on pump vane can be controlled, and the performance of pump is improved and its hydraulic efficiency.
水力机械的分离为三维流动，三维流动的侧向压力梯度产生边界层的二次流动。
The separation flow is three dimensional in hydraulic machine. The pressure gradient in cross direction produces secondary flow in boundary layer.
本文介绍了一种求解二维可压缩紊流分离边界层的正反积分方法。
An integral method associated with direct and inverse mode is presented for the calculation of compressible turbulent boundary layer with separations over airfoil.
以热脉冲加热的主动式加热方式既可用来产生和消除边界层的T-S波，也能用来控制边界层的分离。
The active heating or periodic pulsed heating can be used to excite and cancel the T-S waves and also to control the boundary layers seperation.
叶片型线的选择应满足边界层不分离条件及由欧拉方程——泵的基本方程所确定的理论扬程条件。
The choice of vane curve should satisfy the conditions of boundary layer non-separation and theoretical distance head by Eular equation-the basic equation of pumps.
实验证实了边界层抽吸可以有效地减小激波与壁面边界层相互作用所产生的分离现象。
It has been confirmed by experiments that the boundary layer suction can efficiently eliminate the separation due to interaction of a reflected shock wave with the wall boundary layer.
本文利用三维积分边界层法并结合流线法决定涡层型流动分离。
A 3d integral boundary layer approach is used and coupled with streamline method for determining vortex-layer-type flow separation.
本文利用三维积分边界层法并结合流线法决定涡层型流动分离。
A 3d integral boundary layer approach is used and coupled with streamline method for determining vortex-layer-type flow separation.
应用推荐