按照相似理论的基本原则,设计和确定了用于工业试验煤氧枪的冷态试验模型。采用一维多普勒激光测速仪,测量了旋流流场的轴向速度分布,根据LDV测量值,建立了描述所给旋流场的数学模型。文中指出以余弦函数形式来逼近回流区域内的轴向速度,能获得较现有其它方式更满意的效果。文中还讨论了旋流流场的其它空气动力学问题

特别要注意:膨胀过程是一个等熵过程。 要解决的问题是:已知上游马赫数M及其它流动特性(区域1), 求通过偏转角θ膨胀后的下游(区域2)的特

1.1 Importance of Aerodynamics 1.2 Some Fundamental Aerodynamic Variables 1.3 Aerodynamic Forces and Moments 1.4 Center of Pressure 1.5 Dimensional Analysis: The Buckingham Pi Theorem 1.6 Flow Similarity 1.7 Types of Flow

3.1 Bernoulli’s Equation 3.2 Pressure Coefficient 3.3 Laplace’s Equation 3.4 Uniform Flow 3.5 Source and Sink Flows 3.6 Doublet flow 3.7 Vortex Flow 3.8 Lifting flow over a cylinder 3.9 Visualization 3.10 Summary

2.1 Review of Vector Relations 2.2 Models of the Fluid: Control Volumes and Fluid Elements 2.3 Continuity Equation 2.4 Momentum Equation 2.5 Substantial Derivative 2.6 Fundamental equations in terms of the substantial derivative 2.7 Pathlines, Streamlines, and Streaklines of a Flow 2.8 Circulation 2.9 Stream Function 2.10 Velocity Potential 2.11 Relationship Between the Stream Function and Velocity Potential 2.12 Summary

如果扰动比一个简单声波强,其引起的波前就会比马赫波强产生一 个与来流夹角为β的斜激波,且β>μ。这一比较在图9.4中给出。然而, 斜激波产生的物理机理与上面描述的马赫波的产生完全相同

一、能量方程的各种特殊表达形式 二、总温的计算公式 三、总压、总密度的计算公式 四、临界参数的定义与计算公式 五、特征马赫数(速度系数)M*的定义及计算公式

8.1 INTRODUCTION The purpose of this chapter and Chap. 9 is to develop shock-wave theory, thus giving us the means to calculate the changes in the flow properties across a wave.本章和第九章的目的是推导激波理论,因而得出计算通过激波的流动特性变化量的公式

\The compressibilty correction rule for thin wing The effect of compressibility in 3-D flows is somewhat less dramatic than with 2-D flows, but many of the same effects become important. Many of the same techniques for predicting linear compressibility effects work in 3-D too. For example

在3.2.2节中介绍低速风洞时,我们首次介绍了风洞 扩压器(扩压段)的作用。在那里,扩压器是试验段下 游的一段扩张管道,作用是将试验段的气体的高速度降 低至扩压器出口的很低速度。一般来说,我们可以将扩 压器定义如下:扩压器是将入流速度在其出口处降低的 任意管道(in general, we can define diffuser as any duct designed to slow an incoming gas flow to lower velocity at the exit of the diffuser)