查询词典 mach

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。

The following are the main objections with some real foundation:(1) The campaign of Lysias, which I Mach., iv, 26-34, places in the last year of Antiochus Epiphanes, is transferred in II Mach., xi, to the reign of Antiochus Eupator;(2) The Jewish raids on neighbouring tribes and the expeditions into Galilee and Galaad, represented in I Mach., v, as carried on in rapid succession after the rededication of the temple, are separated in II Mach.

以下是主要的反对与一些真正的基础：（ 1 ）的运动Lysias ，我马赫。，四， 26-34 ，地方在过去的一年里的安提阿哥伊皮法尼斯，是在二转马赫。，十一，对在位安提阿哥Eupator ；（ 2 ）以色列袭击邻国部族和探险到加利利和Galaad ，代表我马赫。，五，为迅速进行继承后重新庙宇，是分开的二马赫。

We then add boundaries delineated forward/backward facing reflected shock, Mechanical equilibrium, M2=1 and reflected shock strong/weak separating conditions on the (M0,q1) map of shih(2004). This is followed by systematically investigating multiply possible three shock theoretical solutions of steady Mach reflections in perfect triatomic gases. Pressure-deflection shock polar solutions are used to help illustrate different solution behaviors of these theoretical three-shock solutions. M0 is flow Mach no. upstream of incident shock, M1 is flow Mach no. downstream of incident shock, M2 is flow Mach no. downstream of reflected shock,q1 is flow deflection downstream of incident shock.

随后本文由石(2004)论文中加入前后分界、机械平衡、M2=1及强弱分界条件，然后有系统地探讨三原子分子理想气体(r=1.2857 )稳态马赫反射参震波理论多重解之交点及其对应之压力-转折角震波极图解，并建构出此三原子分子理想气体稳态马赫反射流场三震波十阶多项式理论解於(Mo，q1)平面上之解域图，其中M0为入射震波上游流场马赫数，M1为入射震波下游流场马赫数，M2为入射震波下游流场马赫数，q1为入射震波下游流场转折角。

In this thesis, we apply the equations of motion of steady Mach reflections and the oblique shock theory to derive polynomial expressions of the forms of f(r,Mo,P1) of downstream sonic and strong/weak separating conditions of reflected shocks of perfect-gas steady Mach reflections. We then obtain polynomial expressions of the forms of f(r,M0) for the limiting Mach angle condition of the above two expressions.

本论文首先应用稳态马赫反射流场运动方程式及斜震波关系式，推导出理想气体稳态马赫反射流场之反射震波下游之音速条件与反射震波之强弱分界条件之曲线解公式，并应用该曲线解公式来推导反射震波俱音速性质於Mach angle条件及反射震波俱强弱分界性质於Mach angle条件之公式。

This paper referred to simulating the supersonic double cone inlet" s flow field of ramjet pill assisted range projectiles at a variety of working circumstances, pressure contours, density contours and Mach number contours of inlet" s flow field were given When cone combination, relative location of cone core and cowl lip, the pressure of outlet, inflow Mach number and angle were changed, flow field and performance parameters of inlet can be affected. Simultaneity, productive mechanism and inducing factors of the inlet surge were also discussed. Then the best working conditions and the best model of inlet were obtained.

本文对冲压增程弹丸所用发动机的双锥超声速进气道在各种工况条件下的流场进行了数值模拟，给出了进气道流场的等压线图、等密度线图和等马赫线图，从而观察在不同的锥尖角组合、锥芯与外罩唇口的相对位置、出口反压、来流马赫数和攻角时，对进气道流场及性能参数的影响，并探讨喘振现象的产生机理及诱导因素，以便确定最佳的工作状态，得到最优的进气道模型。

Single probe ; Parallel Mach probe ; Mach number ; Plasma drift velocity ; Electron temperature ; Ion density

单探针；平行马赫探针；马赫数；等离子体漂移速度；电子温度；离子密度

Wind tunnel investigation is conducted on six different canard configuration models over range of Mach from 0.8 to 2.5.The experiment data analyzes the regulation of rolling characteristics with Mach number and angle of attack,and the effect of rolling characteristics for different configurations is discussed.The rolling damping characteristics are also studied.

通过风洞实验得到了跨、超音速下六种组合模型的气动力数据，由实验结果分析了远程弹滚转特性随马赫数和攻角的变化规律，以及不同鸭式气动布局对滚转特性的影响，此外还分析了远程弹的滚转阻尼特性。

In virtue of Fluent of CFD software, we carry though computation of aerodynamics of an air-to-air missile in different Mach meter and different attack angle and gained movement trend of lift coefficient、drag coefficient and pitching moment coefficient with variety of Mach number and attack angle, meanwhile, we also obtain distributing trend of pressure, temperature and weather velocity.

借助于商业CFD软件FLUENT，对某型空空导弹在不同攻角、不同飞行马赫数的气动力进行了计算，得出了该型导弹升力系数、阻力系数和俯仰力矩系数随飞行马赫数和攻角的变化规律以及导弹表面的压力分布、温度分布和来流速度分布。

The commercial CFD software Fluent was used for simalation of aerodynamic charactirestics of some terminal guided munitions in terminal segment under different affack anyle and mach, the variation lav of or lift coeflienct, drag coeflient and roll moment coefficient with flight mach and attacls angle was obtained, The semulation result shows the caculated aerodynarve parameters can be referend to high accuracy firing table for the terminal guided projectile.

文中主要利用商业CFD软件Fluent对某型末制导炮弹的末制导段在不同攻角、不同飞行马赫数的气动特性进行了数值仿真，得出了该型末制导炮弹升力系数、阻力系数和滚转力矩系数随飞行马赫数和攻角的变化规律。结果表明，计算所得气动参数可以为该末制导炮弹编制高精度射表提供数据依据和参考。

Numerical results demonstrated that there are three kinds of the instability for the under-expanded supersonic jets according to their shock cell structure patterns:(1) the regular reflection shock cell with a single shear layer,(2) the Mach reflection shock cell with two shear layers and (3) the curved Mach stem with a relatively high expansion ratio.

计算结果表明欠膨胀超声速射流的失稳机制根据射流激波结构的特征可分为3种失稳模式：具有规则反射激波结构和单一剪切层特征的射流不稳定性；带有马赫反射激波结构和双剪切层特征的射流不稳定性；具有弯曲马赫杆和高度欠膨胀射流的不稳定性。

I go to school at night.

我是上上学。

Clear Tip Nasal Aspirator: A soft time and gentle suction action makes removing excess mucus easy.

鼻吸明确提示：一个柔软的时间和温柔吸力行动使消除过剩的粘液容易。