全部

1·Finally recent studies of turbulent boundary layer separation are also briefly reviewed.

最后简单介绍了目前在研究湍流边界层分离方面的进展。

2·The negative bowed blades raise the endwall loading and emphasis the boundary layer separation.

叶片反弯增加了端区叶片的负荷，加重了附面层的分离。

3·The introduction of micro pressure sensor array expands ways detecting boundary layer separation point.

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。

4·The control of supercritical airfoil boundary layer separation is adapted using micro-vortex generators.

超临界翼型附面层分离控制适合采用微型涡流发生器。

5·The theoretical analysis and experimental results show that boundary layer separation will produce pressure drag.

理论分析和实验的结果说明：边界层分离将引起压差阻力。

6·The high of vortex generators have their best chord position with an outstanding effect on controlling boundary layer separation.

涡流发生器弦向位置对附面层分离控制效果影响显著，不同高度涡流发生器均有其最佳气动效率的弦向位置。

7·According to the analysis on the boundary layer separation condition, parameter equation of vane curve for centrifugal pump is established.

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。

8·The technology of oil flow and silk thread can reflect effect of the vertex generators controlling the boundary layer separation of the wing truly.

油流和丝线流动显示技术可真实反映涡流发生器对机翼附面层分离的控制效果。

9·The boundary layer separation points, minimum pressure positions on the surface and the drag coefficients are in agreement with numerical solutions and experimental results.

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。

10·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.

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。