The main achievements are summarized as follows : ( i ) the m8 nozzle contour is designed by the characteristic line and the bound layer correction . based on the m7 nozzle , the m8 nozzle is designed by throat approximation 全文取得了如下成果: (一)用特征线加附面层修正的方法设计了m8型面喷管,并在m8喷管的基础上采用喉道拟合的方法生成m7喷管。
Experiments with controlled excitation of primary and secondary instabilities have been performed to study the process leading to the final breakdown of laminar swept wing flow . two types of high frequency secondary instabilities are identified 在人工激励激发基频与定常扰动条件下，施加高频人工激励，研究附面层流流动在高频二次不稳定性扰动的发生与增长过程。
Research results in aboard show that the microjet technique has vast prospects for application . in addition to active flow control , it can also be used as boundary layer control , aerodynamic resistance reduction , combustion strengthening and cooling improvement 国外的研究表明，这种技术除了可用于流动方向控制外，在附面层控制、降低阻力、增强燃烧以及强化冷却等很多方面也有显著效果。
Multi - gap - fowler - flap , while deflecting its rudders , simultaneously extends backwards by relatively large scope , which broaden the overall wing - camber and area , so that more additional lift could be attained through improving air - flow boundary layer 多缝富勒襟翼在襟翼舵面偏转的同时发生较大幅度的后退，增加机翼整体弯度和机翼面积，通过缝隙气流改善附面层状况，因而得到加大的升力增量。
The aerodynamic design of curve of nozzle adopts perfect gas cresco method to calculate non - existence glutinous model surface , the correct boundary layer of the nozzle wall side adopts sivells - payre method , and the calculation of constringency part of the nozzle adopts stock formula 其中,喷管型面气动设计采用理想气体的cresci方法计算无粘型面;喷管的附面层修正采用sivells - payre方法;喷管收缩段的设计采用维托辛斯基公式。
Provide the experimental research scheme to measure and diagnose boundary layer of airfoil . the satisfied results demonstrated that this scheme is correct and efficient . it provides the reliable foundation on analysis of boundary layer characteristics and vortex generators " design 研究结果表明，该方案是正确的，既切实可行、节约了实验经费，又获得了满意的实验结果，为分析附面层特性和涡流发生器的设计提高了可靠依据。
All the improvements included the modifications on the sound velocity , characteristic mach number and the mach number at the grid interface . several 2d flow fields which had shock , shear flow , rarefaction wave , or turbulent boundary layer and the combination of them were computed 该格式改进了声速、特征马赫数的处理方式，对网格界面马赫数进行了修正，并求解了含有脱体激波、斜激波、剪切流、膨胀扇、及湍流附面层等流动特征的复杂流动。
On the rotor blade pressure surface , the dominant frequencies of unsteady surface pressure are the up - stream blade wake passing frequency and its harmonics , and the amplitudes of pressure fluctuations decrease from leading edge to trailing edge 转子叶片吸力面非定常压力受叶片附面层和上游叶片尾迹共同影响，其主导频率为上游叶片尾迹频率及其倍频，但是在吸力面前部气流加速区压力波动幅度沿流向增大，而在吸力面后部气流减速区压力波动幅度沿流向减小。
Finally , the two dimensional flow in the diffuser is calculated , the results show that the change of ma makes an effect to the performance of the diffuser . owing to the accretion of ma , the action of oblique shock waves and the boundary layer pricks up , the flow separates from the wall where the shock waves impinge on the boundary layer more quickly , the cluster of diamond shock waves becomes larger . moreover , by comparing the change of flow field under different structure parameter , it is found that the augment of length of constant area section alter the structure of fluid field little , a smaller area ratio and larger angle of compression section make the diffuser working better 最后,针对扩压器中的二维流场进行了数值模拟,结果表明马赫数对扩压器性能影响较大,随着马赫数的增大,扩压器管道内激波-附面层干扰加剧,流动从附面层分离相应加剧,激波串数目增多;通过比较不同结构参数下的扩压器内流场,发现等直段长度的变化几乎没有改变流场结构,只是对局部流场稍有影响,并且在其它参数不变的情况下,一定范围内减小面积比a2 / a1和增大收缩角有利于扩压器性能的提高。
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。
