音速

Aiming at the strong coupling characteristic during the multi-disciplinary optimization process of hypersonic aerocraft, in order to reduce computing time and increase the feasibility of optimization process, this paper adopted the approximate method to build the responding model between disciplines, In this paper, under the condition of ensuring the engine stable and high efficient , the designing work also consider the whole aerocraft performance sufficiently from the effect of forebody and afterbody.

针对高超音速飞行器多学科设计优化过程中的强耦合特性，为了减少计算时间，提高优化过程的可行性，采用近似的方法来建立学科之间的响应模型，以此来减少每次迭代时所用的大量计算时间。

The designing way of this paper about the forebody and afterbody of aerocraft is based on the wave-rider theory, so design the aerocraft upper and down surface separately, besides keeping the length and thickness of forebody and afterbody constant, to some extent ensure the whole aerocraft design target and avoid the conflict with other disciplines, The flow solver takes use of Euler equations, combining with the technique of the unstructured dynamic meshes.

文中对飞行器前后体设计思路基于高超音速乘波体的思想，将飞行器上下表面进行分离设计，在前后体的长度厚度以及发动机的位置保持不变的条件下，较大程度避免了飞行器整体外形布局的改变，从而一定程度上保证了总体设计的目标，大大缓和了与飞行器其他学科设计时的冲突。

F-15E Strike EagleThis jet, with its two huge afterburning turbofan engines, shakes the ground as it flashes by, just above the runway and just below the speed of sound.

的F - 15 E罢工eaglethis射流，与它的两个巨大的加力涡扇发动机，摇了摇地面，因为它闪烁，刚刚超过跑道和仅低于音速。

I SP* is the vacuum impulse that would be obtained by a sonic nozzle in air-breathing motor work, and thus may be ignored.

i 特*是真空的冲动将得到一音速喷嘴在吸气式发动机的工作，从而可能会被忽略。

In the longer term, air-breathing hypersonic craft could cut the cost of reaching space.

从长远来看，吸入式超高音速飞行器能削减太空之旅的成本。

This paper deals with the numerical methods for transonic flows around airfoil and wing, and its applications.

本论文研究翼型和机翼跨音速定常流的数值方法及其应用方面的问题，主要的工作是

The computational mesh,is generated automatically in terms of analytical/numerical transformation.

由于有限元法在处理复杂边界时的灵活性，近年来正迅速发展成为求解跨音速流场的强有力工具。

An improved engineering approach to flutter analysis of wings with high angle of attack is presented.

跨音速颤振分析是飞行器工程设计中至今未完全解决的关键技术之一。

His team was asked to design a Mach 2 2.5 aircraft, which was then, and probably still is, a nontrivial task-especially when the objective is to create a "cheap" lightweight aircraft. Consider that the force required to overcome drag quadruples when doubling the speed, and what impact that has on aircraft weight.

要知道当飞行速度由单音速变为双音速时，空气阻力会增加至原来的四倍，考虑到因此所需要的动力，及其对机身重量的影响，满足这样的需求，即使是在今天也绝非易事。

On the basis of simulating unsteady viscous flows, coupling the structure dynamics equations, the problem of flutter is investigated for wings, empennage and wing-body configuration.On the basis, many examples, simulating the steady and unsteady viscous flows around wings, are given in this paper.

在模拟非定常粘性绕流的基础上，与颤振运动方程相耦合，分别对机翼、尾翼和组合体流固耦合现象中颤振问题进行了研究，准确求解跨音速颤振临界速度，分析它们在跨音速范围的颤振规律，并研究分析了机翼剖面形状变化对颤振速度的影响。

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。