Transonic Aerodynamics

Understanding the physical behaviour of compressible gas at high Mach number is crucial to design transonic and supersonic airplanes as well as modern gas turbines. This course objective is to cover the basic theories of supersonic aerodynamics, then to apply these to external flows (around airfoil and fuselage nose) and to internal flows (in compressors and turbines).

1. Toolbox : Reminders of fluid mechanics and thermodynamics
2. One-dimensional flow : Normal shock relations
3. Oblique shock and expansion waves : Prandtl-Meyer function ; waves reflections
4. External flows : Critical Mach number ; sound barrier ; bow shock
5. Quasi-one dimensional flow : nozzles
6. Transonic axial compressor flows