5.1 Introduction The properties of airfoils are the same as the properties of a wing with infinite span. However, all real airplanes have wings of finite span. In the present chapter, we will apply our knowledge of airfoil properties to the analysis for finite wings. As we have mentioned in the previous chapter, the analysis for the aerodynamics of wings is separated in two steps.now, we are going on the second-step in Prandtl's philosophy of wing theory

11. 4 PRANDTL-GLAUERT COMPRESSIBILITY CORRECTION The methods that approximately take into account of the effects of compressibility by correct the Incompressible flow results Is called compressible corrections

This chapter mainly deal with the properties of two-dimensional airfoils at mach number above 0.3 but below 1, where the compressibil ity must be considered

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

如上图所示的斜激波在真实情况下有时会碰到固壁或与其它激 波、膨胀波相交,进而发生相互作用,这种现象称为激波的干 扰与反射。本节的目的就是要定性地讨论激波的干扰问题

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

第八章我们讨论了正激波,本章我们讨论斜激波,及超音速流场中的另一个重要特征——膨胀波

本节要点只有 一、计算通过正激波的流动特性变化

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