| 1. | A kind of kelvin type vortex formed by the roll up of the jet shear layer is observed in the experiment
本文还探讨了横流线流分离旋涡的生成机理及转向。 |
| 2. | Furthermore , hair - pin vortex is closely related with high - shear layer structure and spike structure in the pipe flow
此外，发卡涡与圆管流动中的高剪切层结构以及尖峰密切关联。 |
| 3. | The experimental investigations were performed on the impinging shear flow that is comprised with a jet shear layer impinging a plate parallel to the jet
本文对撞击剪切流，即射流剪切层撞击顺流放置的平板的流动，进行了实验研究。 |
| 4. | The possible difficult problems which might be met in numerical and experimental research about supersonic shear layer optics technique are also analyzed in this paper
分析了超声速剪切层光学技术的数值研究和实验研究可能遇到的难点问题。 |
| 5. | Because the symmetrical mode of two free shear layers in the jet is destroyed at x / h = 6 . 0 , the vortex street develops in non - symmetrical ( sinuous ) modes downstream of this station
由于两剪切层的对称性在下游x h = 6 . 0处即被破坏，之后涡街完全按非对称模式发展。 |
| 6. | The problem of aerodynamics and optics in researching aerodynamics window is analyzed , the importance of developing supersonic shear layer optics technique and its applications in aerodynamics window are put forward
分析了气动窗口研究可能遇到的气动问题和光学问题，提出了发展超声速剪切层光学技术并应用于气动窗口研究的重要性。 |
| 7. | Under different positions of a tripping wire or speeds of the side jet , the controlled experiments were made , including the receptivity of the shear layer near jet exit to acoustic excitations , the spatial development of fluctuating velocity and the profiles of mean velocity
在不同绊线位置或不同旁射流流速条件下，研究了射流出口临近剪切层对声激励的感受性，脉动流速向下游的空间演化及平均流速剖面。 |
| 8. | Firstly , the mechanism of self - excited oscillation was introduced . when the water jets from the inlet nozzle flows into the chamber , the momentum exchange between the jet and the liquid in the chamber occurs , thus to form an unstable shearing layer with certain thickness
这是一种崭新的强化换热技术，流体脉动能够造成换热器全程的换热强化，而且自激振荡脉冲射流强化换热技术本身是一种无功强化的方法，无需输入外部能量来产生扰动。 |
| 9. | In order to predict hydrodynamic characteristics a computational system is developed including determination of the pressure distribution on a wing section by use of the conformal mapping method and panel method respectively and of the flow in boundary layer according to the thin shear layer approximation ( tsl ) for navier - stokes equation approach . the wing sections of naca4412 and naca0012 are applied to test the computational system . the numerical inspection shows that the panel method with better precision and the momentum and the displacement thickness of boundary layer can be used to complete this calculation
本文分别用守屋的保角变换法和基于源汇涡分布的面元法，建立了计算桨叶表面压力分布的数学模型；应用纳维-斯托克方程的薄层近似理论模式和有限差分数值方法，建立了计算机翼表面边界层内部流动的数学模型；应用桨叶表面边界层内部粘性流动和外部势流流动在边界上的匹配算法，建立了桨叶表面二相流流动的计算方法和相应的计算机程序。 |
| 10. | Results indicate that the characteristics of cavity flowfield were altered similarly by gas and liquid injection . the local boundary layer or shear layer are modified by injection on upstream / bottom wall of cavity , and the cavity shear layer immediately becomes angled with respect to the main flow direction . the injection on fore wall of cavity has little effect on the characteristics of cavity flowfield
结果表明:气体/液体喷流对凹腔整体流动特征的影响是一致的,凹腔上游/底壁喷流破坏了当地附面层或剪切层,导致凹腔剪切层偏向主流方向;凹腔前壁喷注对凹腔流场特征基本无影响。 |
