mach number的例句大全

the categorization is based on 4 parameters, namely, flight height, flight mach number, engine rotational speed and overload on the engine center of gravity.

选取了飞行高度、飞行马赫数、发动机转速以及发动机重心法向过载等4个参数作为分类的原始依据参数。

the increasing of the incoming flow mach number will decrease the total pressure recovery coefficient.

来流马赫数的增加会造成进气道总压恢复系数的降低。

hypersonic craft is the craft with good aerodynamic shape, high-performance power system and flight mach number above five.

本文研究的高超声速飞行器是指有良好气动外形、采用高性能动力系统、飞行马赫数达到5以上的飞行器。

it can be concluded that the accelerator mode mhd-controlled inlet can improve the inlet performance when the flight mach number is lower than the design value.

研究结果表明，当飞行马赫数小于设计马赫数时加速器模式的磁控进气道可以提高进气道的性能。

the dual-mode scramjet can apply to the wide range of the flight mach number from the supersonic to hypersonic.

双模态冲压发动机满足飞行器由超声速到高超声速的宽广速度范围要求。

because the piston theory is used only locally, this method greatly reduces the limitations of the classical piston theory on flight mach number, airfoil thickness, and angles of attack.

由于局部地使用活塞理论假设，这种方法大大地克服了原始活塞理论对飞行马赫数、翼型厚度和飞行迎角的限制。

aerodynamic force and moment coefficients are given as functions of angle of attack, mach number and control surface deflections.

气动力和力矩系数是迎角、马赫数及控制舵面偏角的函数；

aerodynamic force and moment coefficients are given as functions of angle of attack, mach number and control surface deflections. the propulsion system is a hypersonic air-breathing engine.

该模型包含完整的动力学方程和运动学方程，其中气动力系数和力矩系数是迎角、马赫数及气动舵面偏角的函数，发动机模型为吸气式超声速燃烧冲压发动机。

the thermodynamic analysis equations of combustion heater are given. the flow rates of fuel and oxygen varying with flight mach number are calculated, and the effect of heater pressure on the flow rates is analyzed.

给出了空气燃烧加热器热力计算方程，计算得到了燃烧加热所需燃料流量以及补氧量随模拟飞行马赫数变化曲线，分析了加热器压力对加热所需燃料流量以及补氧量的影响。

the results presented by this model agree well with those of solving unsteady euler equations. this model greatly reduces the limitations of the classical piston theory on flight mach number, airfoil thickness, and angle of attack.

通过与非定常Euler方程的比较，证明该气动力模型具有较高的数值精度，放宽了原始活塞理论对翼型厚度、迎角、马赫数的限制。

a set of design parameters were given. the simulation results show that the application of mhd control technology to inlet design can effectively regulate combustor incoming flow state, improve specific impulse and extend the operating range of flight mach number.

给出了一组磁控进气道设计参数，仿真结果表明采用磁控进气道技术可以有效地调节燃烧室进口来流状态，提高比冲，拓宽飞行马赫数范围。

at high flight mach number, the performance of the forebody/ inlets designed by the two methods is approximate. at low flight mach number, the starting performance of forebody/ inlet designed by the method of constant shock wave intensity is better.

采用等激波强度和等激波角度方法设计的进气道在高飞行马赫数下的性能相近，在低飞行马赫数下，采用等激波强度方法设计的进气道起动性能较优。

design of an adaptive control augmentation stability system for fighter aircraft whose flight altitude and mach number vary

飞机在变高度和变马赫数下自适应控制增稳系统的设计

airbreathing hypersonic technology studies the technology of flight vehicle for long-distance hypersonic flight in atmosphere layer or trans-atmosphere layer at flight mach number above 5.

吸气式高超声速技术是指飞行马赫数大于5、以吸气式发动机及其组合发动机为动力、在大气层和跨大气层中实现高超声速远程飞行的飞行器技术。

the ballistic flight used gliding flight is a way to increase the range of rocket, but because of the constraint conditions included the flight mach number, running time of engines and the angle of emission, make the ballistic characteristics of ballistic flight become very complex.

采用滑翔弹道飞行是一种增加火箭弹射程的方法，但由于受到飞行马赫数、发动机工作时间和发射角度等条件的约束，使得滑翔弹道的弹道特性变得很复杂。

For that with longer flight time and higher Mach number, a concept of thermal management system using endothermic fuels as heat sink was advanced.

对飞行时间长，飞行马赫数高的飞行器，提出了以吸热型碳氢燃料为热沉的热管理方案；

for the further supersonic range, performance losses increase slightly with increasing mach number.

在继续的超声速范围内，性能损失随外流马赫数增加只有小幅增长。

the results show that, under the conditions of high altitude, the flame tube wall temperature of the same axial position is increased with the increase of mach number;

结果表明：在高空条件下，火焰筒同一轴向位置的壁温随马赫数的增大而升高；

numerical study of mach number at the 3-d sidewall compression hypersonic inlet and isolator

马赫数对侧压式高超音速进气道及等直隔离段三维内流场的影响的数值分析

There are shock lets in the mixing layer with convective Mach number 1.2.

高对流马赫数混合层中存在较弱的小激波间断.