激波

Based on momentum theory and shock wave gas dynamic theory, jet equivalent body idea and bow sharp wave mathematic formula is brought forward.

利用动量定理和激波理论分析方法，提出了喷流等效体的概念，推导了等效体弓形激波方程。

Then the reflected shock wave produced by the parabolic reflector in resonator cavity frequently penetrated the flame, which led to continuous flame excitation.

共振腔抛物面的不同形状引起激波聚焦位置的变化，会影响激波和火焰的相互作用，使起爆提前或推迟，甚至不起爆。

On the western side of the central normal of the disturbance source in the heliospheric equatorial plane, the double shock pair structure is more evident, and the longitudinal span is wider than those on the eastern side.

双重激波对在子午面内相对扰动源中心法线基本对称，而在赤道面内则不对称：扰动源中心法线西侧双重激波对结构更为明显，所跨经度范围宽于东侧。

On the western side of the central normal of the disturbance source in the heliospheric equatorial plane, the double shock pa ir structure is more evident, and the longitudinal span is wider than those on t he eastern side.

双重激波对在子午面内相对扰动源中心法线基本对称，而在赤道面内则不对称：扰动源中心法线西侧双重激波对结构更为明显，所跨经度范围宽于东侧。

At first, numerical simulation are made on the temporal developing gas-phase mixing layer where the convective mach number is in the region of subsonic(0.5) and transonic(0.8). For the temporal problem where Mc is 0.5, researches where the computational field contains different numbers of initial disturbances(so-called n period problem) are made respectively, and vortex's types of evolution in mixing layer including different numbers of initial disturbances are investigated; For the temporal problem where Mc is 0.8, the distinct shock let structure is obtained, and its mechanism is analyzed at the same time.

文中首先对对流马赫数为亚声速(0.5)、跨声速(0.8)的时间发展单气相混合层作了数值研究，对Mc为亚声速单气相时间发展混合层，分别研究了计算域包含不同数目的初始扰动周期问题，考查了不同周期数的混合层中涡的不同演化方式；对Mc为跨声速的单气相时间发展混合层，得到了清晰的小激波结构，同时分析了小激波的形成机理。

It is shown that maximum temperature value of the field's will rise while the Mach number increases. After the Mach number exceeds one, a clear bowshock is obtained in the simulation result, and the Mach angle decreases along with the Mach number. Those are consistent with theoretical results. While the Mach number is 3.5, even the radome inside is adiabatic, the maximum temperature is below 1000K. So the CVD diamond thick film radome can meet practical requirement of flight at 3.5 Mach number.

研究发现，随着马赫数的增加，温度场中最大温度值也随之增大；在马赫数大于1时，会产生明显的弓形激波，且激波的锥角随马赫数增加而减小，这与理论结果相一致；当马赫数为3.5时，即使在头罩内壁绝热条件下，温度场中最高温度值也在1000K以下，表明CVD金刚石厚膜可以满足Ma=3.5的实际飞行要求。

At the chapters of theory analysis,constitutive equation of dusty is deduced from the results of the experiment and related theories about oblique shock wave.after that relationship of parameters reflecting flow-field characteristic are deduced from theories of shock wave polar .The paper set up conservation equations depicting gas and solid flow-field by double fluid model,thus equations and constitutive equation of granular phase form closed equations.then the paper uses AUSNT vector splitting method to numerically calculate the equations.

理论部分主要包括：利用实验测试结果以及斜激波理论测试出该堆积粉尘的本构方程，然后利用和激波极曲线理论得到反映流场特征参数的变化曲线；本文还利用双流体模型，建立了描述气—固两相流动的守恒型方程组，与本构方程一起构成封闭方程组。

Using this system, we studied jet impinging cone and found some new shock wave structures.

利用这一系统，研究了射流冲击流场中激波结构的一些变化规律，发现了一些新的激波结构。

This chapter to some extent exists independently and the discussion has been related inevitably to the concept of leading edge space curve bent.

第二章建立激波曲面的螺面模型，这是研究三维激波曲面掠的必要基础。

The evolution of the half-peak width of the relative density increment pulse with respect to slow wave also demonstrates the close relation to Δp. Its minimum w〓 decreases with the increase of Δp, which means, slow wave will steepen with the enhancement of Δp and may evolve into slow shock eventually. Numerical results also indicate that the propagation velocity of fast and slow wave increase when Δp increases.

对强扰动情形(Δp＝5)，通过考察相关物理量的径向分布，并借助于对物理量沿波动阵面法向分布的讨论，可以初步判断出由强扰动所造成的慢模磁声波在传播过程中逐渐陡变而演化为慢激波，慢激波在进入日冕前已在色球层中形成，并在此后的传播过程中始终保持这一性质。

In the United States, chronic alcoholism and hepatitis C are the most common ones.

在美国，慢性酒精中毒，肝炎是最常见的。

If you have any questions, you can contact me anytime.

如果有任何问题，你可以随时联系我。