音速

喷气机正在以音速飞行。

The jet plane is flying at the velocity of sound .

所追踪的技术目标是不受温度、音速影响的压力平台效应。

The traced technical target should be pressure platform effect that is not affected by temperature and velocity of sound .

这架飞机的速度将是音速的两倍。

The aeroplane will travel at twice the speed of sound .

这比大多数亚音速飞机的飞行高度高20,000英尺。

This is 20,000 feet higher than most subsonic airliners .

目标是以大约2马赫的速度飞行，也就是音速的两倍。

The aim is to fly at about Mach 2 , twice the speed of sound .

这架新式飞机以两倍于音速的速度飞行。

The new airplane flies at twice the speed of sound .

亚音速运转连续波COIL输出功率的经验公式

The formula for estimating the output power of subsonic COIL

即使中国地区亚音速飞机排放的NOx增加一倍，这个影响仍然比较小。

When subsonic aircraft NOX emission over China is doubled , its influence is still relatively small .

并同ISO法作了比较，证明了串接音速排气法优于ISO法。

After comparing SSE Method with ISO Method , the former is shown to be superior to the latter .

由于中国地区亚音速飞机排放的NOx造成的NOx的增加不超过10pptv，而且臭氧增加小于0.4ppbv。

The NOX increases by less than 10 pptv by virtue of subsonic aircraft NOX emission over China , and ozone changes less than 0.4 ppbv .

TVD格式与高超音速气动加热数值模拟

TVD scheme and numerical simulation of aerodynamic heating in hypersonic flows

用多重网格TVD方法求解三维高超音速粘性流场

Multigrid and TVD Scheme for Three Dimension Hypersonic Viscous Flowfield

高超音速流场的隐式TVD格式并行计算

Parallel Calculation of Implicit TVD Scheme for Hypersonic Flowfield

对一种新的测试气动元件流量特性的方法进行了研究，即利用等温容器的放气曲线来测量气动电磁阀的音速流导C和临界压力比b。

This paper studies , a new method for measuring flow rate characteristics of pneumatic solenoid valves , namely measuring sonic conductance C and critical pressure ratio b of pneumatic solenoid valves using discharge pressure curve of isothermal chambers .

CARET进气道亚音速气动特性研究

Studies of a Caret Inlet at Subsonic Speeds

发展了一种运用定常CFD方法和活塞理论求解超音速、高超音速非定常气动力的新方法&当地流活塞理论。

Employing Euler based steady solution and piston theory , a new method ( we call it local piston theory in this paper ) to solve supersonic or hypersonic unsteady loads has been developed .

用激光诱导碘荧光的方法对高超音速低温喷管的混合性能进行了测量，并用CFD软件FLUENT模拟了喷管的流场。

The flowfield of hypersonic low temperature ( HYLTE ) nozzle in continuous wave DF / HF chemical lasers was visualized by laser induced iodine fluorescence ( LIIF ) and simulated by the CFD software FLUENT .

本方法是基于对FW-H方程的准确求解，并限制螺旋桨叶尖相对速度为亚音速。

The blade tip speed is limited to subsonic . The formulation is based on the FW-H equation .

本文介绍在NH-1三音速风洞中进行测力试验时使用的拐角六分量应变天平的研制情况。

A corner six-component strain balance used for measuring forces in NH-1 trisonic wind tunnel is described in this paper .

然后采用IFFT算法和自适应数值积分算法计算二维积分，得到了低音速、跨音速和超音速移动荷载作用下动力响应的数值结果。

Coupled IFFT algorithm and adaptive quadrature algorithm was employed to compute double integrals in the analytical solutions . All the subsonic , transonic and supersonic cases were computed .

根据实验数据，由热力学关系式得到了HFC152a在四个温度下的理想气体比热容和第二音速维里系数。

The ideal gas heat capacity as well as the second acoustic virial coefficient has been deduced from the sound velocity measurements .

根据2000年亚音速飞机排放的NOx，利用三维全球化学输送模式（OSLOCTM2）研究亚音速飞机排放的NOx对中国地区NOx和臭氧的影响。

A three-dimensional global chemistry transport model ( OSLO CTM2 ) is used to investigate the impact of subsonic aircraft NOZ emission on NOX and ozone over China in terms of a year 2000 scenario of subsonic aircraft NOX emission .

一是通过创造性地仿照亚音速客机机身布局方法，提出适用于SSA的机身布局方法，推出SSA乘客总数对机身布局的要求。

At first , a fuselage arrangement technique applicable to SSA was derived from imitating subsonic airliner fuselage arrangement method in a creative way . The demand of the passenger total to fuselage arrangement was indicated .

采用亚音速偶极子格网法计算非定常气动力，用状态空间法计算翼面颤振速度，利用最佳控制理论进行最优控制设计，结构固有振动用谱变换Lanczos方法求得。

The optimal control theory is introduced to design the control law . Natural vibration modes are obtained by spectral transformation Lanczos method . The FEM is used to simulate the wing structure .

对滑跃式高超音速巡航飞行器的动力技术进行了初步研究，分析了采用火箭基组合循环发动机（RBCC）方案所需的燃料消耗。

Finally dynamic technology of soaring hypersonic cruise vehicle was preliminarily investigated . The fuel consumption of rocket based combined cycle ( RBCC ) for the soaring hypersonic cruise vehicle was analyzed .

这种方法特别适合于高超音速非定常流场，已研制成完整的测量系统LVG-1。

This method is especially good for measuring unsteady hypersonic flow field . An integrated measuring system LVG-1 has been devel - oped .

本文将Davis的量级分析方法改用匹配渐近展开方法，作为一级近似推导出了高超音速化学反应粘性激波层方程。

In the present paper , the method of matched asymptotic expansions is introduced to the Davis ' viscous shock layer theory , and the result of the first order of approximation leads to the same hypersonic chemically reacting viscous shock layer equations as with the Davis ' method .

针对开敞空间可燃气云爆燃（简称为UVCES）过程所产生的爆燃波为亚音速传播特点，对开敞空间可燃气云爆燃场进行数学求解。

Aiming at the characteristic of deflagration wave occurring in course of UVCES transfers at a speed of sub sound , qualitative solution was gained .

模型发散动压的计算是利用NASTRAN的柔度法和自行开发程序的模态法进行的，两种方法均采用亚音速偶极子格网法气动力理论的定常部分进行气动力的计算。

The divergence pressures of these models were calculated by the flexibility method of MSC / NASTRAN and the mode method developed by the authors , while the steady aerodynamics of the subsonic Doublet Lattice method is used for aerodynamic calculation in both the methods .

首先，研究了高超音速零攻角小球头锥边界层的稳定性特点，并用e-N法进行了转捩预测。

Firstly , stability of a hypersonic boundary layer on a blunt cone with small nose bluntness at zero angle of attack has been investigated and the transition location was predicted by the e-N method .