Introduction to Compressible Flow
This course introduces the theory of compressible flows (gases) and the mathematics representation of different flow regimes. Students will learn about the governing equations of general compressible flows and special cases such as inviscid and irrotational flows. The course will cover the following topics: 1D-flow, converging-diverging nozzle, normal and oblique shock definitions and practical examples for aerospace applications, Mach waves, wave equation, shock tube, transonic flow, supersonic flow, method of characteristics, and an introduction to hypersonic flows. Practical examples of aerospace applications such as turbomachinery flows, flow past an airfoil and a 3D wing will be included.
Topics
- This course intends to introduce undergraduate engineering majors with an interest in aerospace engineering to the theory and concepts of compressible flow regimes, their definitions, governing equations, and techniques to evaluate flow characteristics using a variety of real-world aerospace use cases including both internal and external flows.
- • Define compressible flow and be able to provide a quantitative estimation of a flow to be compressible. • Be able to explain various terms in the governing equations of compressible flows and describe assumptions and derive equations for special flow types such as inviscid flows, quasi 1D flows, and irrotational flows. • Explain the flow behavior and characteristics in subsonic, transonic, supersonic and hypersonic flow regimes.
Official catalogue course objectives and student learning outcomes
Sources
- Course catalogue ↗2026-2027