马赫波

爆轰马赫波载荷特性及传播规律实验研究

An experimental investigation on the loading performance and propagation law of detonation Mach waves

本文介绍了可以直接观测马赫爆轰波的形成、生长规律及其传播过程的实验方法，并对马赫爆轰波参数进行了计算。

The parameters of Mach detonation waves have been computed .

烟板法研究马赫反射三波点轨迹

The investigation of Mach reflection triple point trajectory by smoky plate method

本文介绍激波管中用烟板法测量马赫反射三波点轨迹的一种实验方法。

The smoky plate method is used in measurement of Mach reflection triple point trajectory .

水平支管中马赫反射三波点迹线始于右尖点下游。

The triple-point trajectory characterizing Mach reflection locates downstream of the right corner in the horizontal branch .

实验测量得到了设计安装角及变工况下叶片表面压力、叶片表面等熵马赫教及波系结构随叶栅进口气流角的变化，并对叶栅内部及出口流场进行了纹影照相。

The designed fixing angle , surface pressure of blade under varing working conditions , the iso-entropy Mach number and the variation of waves structure with air intake 's flow angle are obtained through experiments .

文中给出了绕射波的波形以及平面激波绕过矩形障碍物后与地面相互作用而产生的从规则反射到马赫反射的波系图案。

This paper presents the results which are the form of diffracting shock wave and the shape of regular reflection and Mach refraction on shock tube , when a plane shock wave diffracted around a rectangular obstruction .

前掠机翼拥有许多优越的气动特性，如临界马赫数高、波阻小和翼尖失速度大等优点。

Forward-swept wing has many advantages in aerodynamic characteristics , such as high critical Mach number , low wave drag and no wingtip stalling .

氮化物纤维具有优异的高温力学性能和热稳定性，是高马赫数飞行器透波材料的理想增强体。

Due to the excellent high temperature mechanical properties and thermal stability , nitride fibers are potential to be the desirable reinforcement materials of high-Mach-number aircrafts .

前掠翼飞机气动特性优越，具有包括临界马赫数高、波阻低和克服翼尖失速等很多优点，但扭转发散问题也是制约前掠翼机广泛实用化的障碍。

Torsional divergence problem is an obstacle in the application of forward-swept wing aircraft , despite its many advantages in aerodynamic characteristics , such as high critical Mach number , low wave drag and no wingtip stalling .

发现火箭发射噪声与马赫反射、冲击波的叠加和二次燃烧等因素有关，而这一切都与发动机的相对位置的不同而变化。

In the meantime , the rocket launching noise correlated a Mach reflection , shock wave addition , and the second deflagration is found , and the position change on corresponding position of the impinged object and rocket engine .

该方法可以计算穿透激波的强度和形状，马赫反射时三波点的轨迹，马赫杆的强度和几何形状，以及锥面峰值压力的大小。

This method can be used to calculate the strength and shape of the transmitted shock , the triple-point trajectory of Mach reflection , the strength and shape of the Mach stem and the peak pressure on the cone surface .

本文利用Whitham绕射理论，给出了球面激波对平面绕射时马赫杆的近似解，同时求得了马赫反射三波点迹线及壁面超压。

This paper derives an approximate solution to the Mach stem of diffraction of a spherical shock wave by a plane using the diffraction theory proposed by Whitham . Also , it gives the loci of Mach triple points and the overpressure on the plane .