Deal with high Mach number
The potential assumption restricts the max. Mach number to 1.3. However, higher Mach numbers can appear:
- in high freestream AoA/Mach cases
- at the wingtip's trailing edge
The first scenario will induce strong shockwaves. These can be detected and non-isentropic relationships could be used to compute the flow properties around the shocks. This would require to:
- implement a shock detector
- improve the data structure so that it contains the faces of the elements (finite-volume type)
- implement the Rankine-Hugoniot relations and check how they affect the flow properties
The second issue appears due to the tip vortex which, if resolved, has an infinite core velocity. Such high velocities and associated Mach numbers could be damped by using a Padé assumption locally. This would require to:
- allow the user to define a physical region around which the flow properties will be damped
- map the fluid elements to either undamped or damped flow properties (
std::map<Element *, F0ElRho[Clamp]>
)
Additionally, the velocity should also be damped (currently, only the density, Mach and pressure are).