Transonic Aerodynamics

Lecturer(s): Stéphane AUBERT
Course ⋅ 20 hStudy ⋅ 8 h


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).

Palabras clave

compressible flows, supersonic, show wave, expansion wave, interactions, analytical methods


  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

Learning Outcomes

  • To elaborate and to apply formulations adapted to compressible and transonic flows
  • To understand transonic aerodynamics phenomena in external and internal flows
  • To judge the accuracy of models to estimate quantities of interest from a design point of view


Final mark = 100% Knowledge Knowledge = 100% final exam