The results show : laser beam far field intensity distribution deflect to the wave length increasing direction , the influence to laser beam far field intensity distribution of different inflow mach number is little than the influence of different inflow pressure ; flow field has more aberration to 1 . 315um laser beam than to 10 . 6um laser beam 研究表明激光束远场强度分布都向流场光程增大的方向偏折，喷流出口马赫数的变化对激光束远场强度分布的影响较小，喷流出口压力的变化对激光束远场强度分布的影响较强；在相同的流场结构下，流场对波长1 . 315 m激光束的干扰要明显强于对波长10 . 6 m激光束的干扰。
Based upon practical engineering applications , the variant separating - variable algorithms of hyper - surface fitting for arbitrary multivariate scattered data are presented by separating positional variables in a spatial domain from certain physical variables such as time , mach number , angle of attack and so on , followed by their comparison . when compared with existing scatted data interpolation algorithms , the new ones are more effective . a sufficient condition to exchangeable order of separation is obtained and order of continuity on the hyper - surfaces above is discussed 三、以实际工程应用为背景，将具有某种物理意义的量(如时间、 ma数、迎角等)与空间位置变量分开处理，给出任意散乱数据超曲面拟合变量分离的各种算法，对它们进行了算法的分析比较，获得了分离次序可交换性的充分条件，给出了变量分离法构造的超曲面的光滑阶。
A parametric analysis of the inviscid effects of leading edge sweep , sidewall compression , width - height ratio , cowl position and inflow mach number on spillage is finished . numerical simulations are completed for a series of inlets at various flight height and velocity . the research indicates that the area of spillage window , which is mainly determined by the position of the cowl , significantly influences the spillage characteristic of the scramjet inlet 阐明了侧板后掠的侧压进气道设计参数对构型溢流影响;对不同侧板配置方式的侧压式进气道进行了数值模拟,通过对比分析,发现由唇口板的位置所决定的溢流窗面积的大小对进气道溢流特性的影响显著。
The micro boundary layer experiment is carried out from 8mm to 14mm of a 15mm - long micro plane . re numbers vary from 35 , 000 to 150 , 000 and 4 different mach numbers are selected . some new characters are discovered , such as velocity curve factor is smaller than that of well developed normal scale turbulence boundary layer 微尺度平板边界层实验选取从总长度为15mm的微平板前缘8mm到14mm之间的7个站位, 4种马赫数, 13个不同雷诺数(从35000到150000 )的实验状态,发现了该尺度下边界层流动的一些新的特点,如形状因子比常规大尺寸下充分发展湍流状态的形状因子更小等。
The effects of such elements as primary flow total pressure , flow rate , degree of fuel rich , nozzle structure , flying speed and secondary combustion on ejecting mode performance were researched . it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0 . 7 . to deeply analyze thrust augmentation mechanism in low speed range , the research was further continued by changing secondary combustion organization and aft - body configuration 研究了一次流总压、流量、富燃程度、喷管结构、二次流来流速度、二次燃烧组织对引射模态性能的影响，发现实验样机构型在0 . 7ma以上的飞行条件下可以获得推力增强，而在0 . 7ma以下无推力增强。
In this thesis , hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested . with increasing mach number of inflow gradually , the hypersonic sidewall compression inlets can self - start . compared with the hypersonic sidewall compression inlet starting directly , characteristics are different . moving cowl , decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out 其次,在数值模拟结果的基础上,设计了实验模型和装置并在马赫3 . 85的风洞中进行了移动唇口板减小内收缩比实现侧压式进气道自起动的风洞实验,验证了数值模拟的结果。
The velocity distributions , the relative mach number distributions and the flow trace distributions are visualized , and the reasons , which cause bad aerodynamic losses and make the flowfield complicated , are analyzed , including wake , secondary flow , separated flow and the interaction between shock and boundary layer 显示压气机内的速度场、相对马赫数分布及流动迹线分布等，并分析造成严重损失及使流场趋于复杂紊乱的原因，包括尾迹、二次流、分离流及激波/附面层干扰等现象。
On the basis of these results , the relations of total - pressure recovery coefficient or flow coefficient and flight mach number , angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting , then the mathematical model of the inlet is established 根据流场计算结果并利用超曲面拟合方法建立了进气道总压恢复系数、流量系数与飞行马赫数、进气道攻角及二级可调斜板角度之间的关系，由此得到了二元混压式超声速进气道数学模型。
