马赫角

词组短语

mach angle

与马赫角相关的网络例句 [注：此内容来源于网络，仅供参考]

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。

The improved e-N method can also yield results well agree with those obtained by DNS.4 The transition prediction for boundary layers on cones with different key parameters such as angle of attack, cone half angle and the Mach number of the coming flow, have been made, to show the reliability of the modified e-N method.5 For the calculation of base flow, boundary layer equations can be used in the case of small angle of attack.

但是它要依赖于对初始扰动的正确预估，这显然又取决于更多飞行数据的积累和分析。e-N方法的转捩预测结果与直接数值模拟得到的结果也吻合较好。4通过对不同来流攻角、不同半锥角和不同马赫数的三维圆锥边界层的转捩位置进行预测，证实了改进的e-N方法对于三维边界层转捩预测是可靠的。5对于基本流的计算，边界层方程可以用于小攻角的情况，其计算量远远小于直接数值模拟，但背风面的剖面不可靠。

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。

Finally, based on the optimized configurations,the lift coefficients, drag coefficients and lift-drag ratios were calculated with hundreds of in-flow Mach numbers and angle of attacks.Some interesting phenomena occured and were depicted.

最后，针对得到的优化外形，计算了不同来流马赫数和攻角下的流场并分析了升力系数、阻力系数以及升阻比随马赫数和攻角变化趋势，得到了一些有趣的规律。

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 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。

From the shadowgraphs, it is observed that the patterns of a plane incident shock wave reflected from the parabolic reflector can be either a regular reflection or a Mach reflection which depends on the shock wave strength and the reflector geometry.

由流场观察得知，入射震波强度较小、收敛角较小的，震波经反射体的反射型态趋向於正规反射，当入射震波强度增强、收敛角增大时，反射型态则会由马赫反射型态再转为正规反射型态。

With this method a model of the large offset, highly compact intake is made and tested meticulously at low and high speeds. In the paper the distribution of the total pressure at the exit section and the static pressure along the wall of the intake is given at low speed, and the performance of the intake has measured at different Mach numbers, incidences and yaws.

并借鉴S形进气道的设计方法完成了高偏距、短扩压埋入式进气道的设计，并对该埋入式进气道的高、低速性能做了细致的研究，给出了0.1马赫数下进气道出口截面上的总压分布、总压畸变、壁面静压分布，以及0.5～0.8马赫数范围内，该进气道模型在-7°～10°攻角范围和8°侧滑角范围内的性能。

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。

Using the methods and software of this thesis some flow regulations, design principles and criteria are developed to give more accurate and credible aerodynamic coefficients of ailerons.

模拟了舵面在不同缝隙、不同舵面偏角及来流迎角下的复杂流动问题；结合对舵面气动特性的风洞试验结果的分析，归纳总结出舵面铰链力矩随缝隙、舵面偏角、来流迎角、马赫数的变化规律，探讨了如何将数值计算与风洞试验相结合为飞机设计提供准确、可信的舵面气动特性参数的方法。

与马赫角相关的网络解释 [注：此内容来源于网络，仅供参考]

angle, dihedral：二面角,上反角

"提早角","angle, advance" | "二面角,上反角","angle, dihedral" | "马赫角","angle, Mach"

laval nozzle：拉瓦尔喷管

perfect gas 完全气体 | Laval nozzle 拉瓦尔喷管 | Mach angle 马赫角

Mach angle：马赫角

m center m 中心 | mach angle 马赫角 | mach cone 马赫锥

Mach angle：马蒜角

maccormack scheme 麦科马克格式 | mach angle 马蒜角 | mach cone 马蒜锥;马赫锥

Mach Angle Cone：马赫角锥

987 Mach 马赫值 | 988 Mach Angle Cone 马赫角锥 | 989 Mach number 马赫数

angle, Mach：馬赫角

"二面角,上反角","angle, dihedral" | "马赫角","angle, Mach" | "压力角","angle, pressure"

Mach cone：马赫锥

mach angle 马赫角 | mach cone 马赫锥 | mach number 马赫数

Mach cone：马蒜锥;马赫锥

mach angle 马蒜角 | mach cone 马蒜锥;马赫锥 | mach criterion 马赫判据

Mach cone：马赫锥,扰动锥

Mach angle 马赫角 | Mach cone 马赫锥,扰动锥 | Mach diamond 菱形激波

Mach：马赫

剪应变是物体承受剪应力(shearing force) 时的角变形小于1 马赫(Mach)的速度. 太阳系(solar system) 中心的星球(star) . 典型的主序矮星(参见见solar constant). 太阳表面的光球层(photo-sphere)形成透明内部和由于局部温度下降至约4000K,