超声速

The good design of this device is very important to accomplish flow control and stability of the aircraft construct. The contour of scarfed reversal nozzle has many discontinuous points and a step at supersonic zone. So it can generate a series of expand waves and shock waves, and accomplished with flows separation and reattach.

斜切反喷管作为导弹常用的推力终止装置，能够可靠地完成发动机与有效载荷的分离，它的设计水平对提高导弹命中精度和武器装备的作战性能尤为重要；超声速开式空腔作为流动控制装置，具有减小阻力、增加燃烧混合、延缓边界层分离等作用，但同时也会带来严重的压力波动和噪声，其合理的设计对流动控制的实现以及飞行器结构的稳定性至关重要。

A numerical simulation was conducted for a fixed-geometry two-dimensional mixed-compression supersonic inlet with sweepforward high-light and "X" type missile configuration. The results indicate:(1) The total pressure recovery declines with the rise of the free stream Mach number, while the mass flow ratio rises firstly and then declines when its maximum value is obtained at the design point.

针对一种定几何二元倒置&X&型混压式超声速进气道开展了数值仿真研究，结果表明：随着来流马赫数的增加，进气道总压恢复系数下降，而流量系数却先上升，在设计点达到最大值后下降。

This is the first step for H〓 pilot flame igniting the combustible, two phase flow of hydrocarbon.

目的是为了弄清燃料的混合机理，为以后两相超声速燃烧的数值模拟打下基础。

The supersonic flow and combustion were simulated by the method of large eddy simulation.

并采用大涡模拟方法数值模拟了超声速流场中气动斜坡的流动及燃烧特性。

The results demonstrated that supersonic airflows will form a low-frequency oscillation in the combustor after the inlet cover is open, and the attenuation of the oscillation is very slow.

计算结果表明，在进气道整流罩打开以后，超声速气流会在燃烧室通道内形成振幅衰减较慢的低频剧烈振荡。

Part three: numerical simulation on the supersonic chemically reacting flow field in the combustors.

主要工作包括三部分：第一，雾化后的燃料液滴和气态燃料在燃烧室的超声速气流中混合问题的数值模拟。

The results show that the cavity can change the waves in combustors,and facilitate the mixing of hydrogen and air for easier combustion.

采用有限体积法求解可压缩N-S方程及组分方程，对三种不同结构的超声速燃烧室进行了数值研究。

This is impractical for engineering problem. It is necessary to break the shear layer in order to enchance mixing. It is very useful for combustor design with cavity or dual-cavity. In such combustor the fuel jet can break the

要使超声速混合增强，必须打破稳定的剪切层，燃烧室采用凹槽或双凹槽设计是一种行之有效的方法，它产生的燃料射流就能打破剪切层，从而使混合和燃烧效率进一步提高。

For example, when passing at low altitude supersonic aircraft, when the head and tail of the aircraft will have the pressure and density of mutations through the surface formed after the N-shaped shock wave reflection, reached the ground sounds like explosions, this special sound of noise is called the H -.

例如，当超声速飞机在低空掠过时，在飞机头部和尾部会产生压力和密度突变，经地面反射后形成N形冲击波，传到地面时听起来像爆炸声，这种特殊的噪声叫做轰声。

It turns out that the flow and noise characteristics are quite complex and different from those of incompressible jets due to existence of quasi-periodic shock cell structures.

超声速射流是一般工业和军事工业中得到广泛应用的重要流动现象，对其流动特性和声学特性的研究，在实际应用和学术研究上有重要的理论价值和实际意义。

According to the clear water experiment, aeration performance of the new equipment is good with high total oxygen transfer coefficient and oxygen utilization ratio.

曝气设备的动力效率在叶轮转速为120rpm～150rpm时取得最大值，此时氧利用率和充氧能力也具有较高值。

The environmental stability of that world - including its crushing pressures and icy darkness - means that some of its most famous inhabitants have survived for eons as evolutionary throwbacks, their bodies undergoing little change.

稳定的海底环境─包括能把人压扁的压力和冰冷的黑暗─意谓海底某些最知名的栖居生物已以演化返祖的样态活了万世，形体几无变化。