(BQ) Part 2 book "Aerodynamics for engineering students" has contents: Compressible flow, airfoils and wings in compressible flow, viscous flow and boundary layers, flow control and wing design, propulsion devices. | CHAPTER Compressible Flow 6 LEARNING OBJECTIVES • Learn how elementary thermodynamics is incorporated into fluid dynamics to describe compressible flow. • Develop one-dimensional analysis to solve for fluid and thermodynamics property changes through a steady normal shock wave. • Apply results of the analysis of steady normal shock to understand flow through oblique shock waves. • Learn about Prandtl-Meyer expansion flows and how they differ from oblique shocks. Thus far in this text the study of aerodynamics has been almost exclusively restricted to incompressible flow. For incompressible flow the density and temperature of the fluid are assumed invariant throughout the flow field, and energy is exchanged between kinetic energy and pressure only. This is only suitable for the aerodynamics of low-speed flight and similar applications. As flow speeds rise, thermal energy per mass (or per volume) also begins to change, leading to a more complex fluid model and to even more interesting aerodynamic phenomena. One prominent contemporary example of fluid physics and flight research in compressible flows is known as “quiet supersonic” flight, in which the aircraft shape, typically the underside toward the nose, is designed to produce as weak a shock wave as possible in hopes of enabling regular overland supersonic flight [45]. Analyzing, computing, or measuring the impact of small changes in aircraft shape on the pressure wave miles away from the aircraft is a true challenge. The generation and transfer of heat due to viscous effects and heat conduction are also significant in the boundary layer, but these and other viscous effects are not considered in this chapter. The chapter begins with what is known as quasi-one-dimensional (Q1D) flow. This is an approximate approach suitable for flows through ducts and nozzles when changes in the cross-sectional area are gradual. Under this circumstance, the flow variables are assumed to be uniform across a cross-section so that they vary only in the
