Case description 20% bump in a channel inviscid flow unsteady upstream Mach number (sinusoidal oscillation from 3 to 2.4 to 3.) MACH=3.+.6*(cos((t-.1)*6.28)-1.)*step((t-.1)*(1.1-t)) Numerical parameters 1600x320 quad mesh morphing functions are MORPH_X = 5*X
MORPH_Y = Y+step(1-(sqr(x-.4)/0.04))*(1-sqr(x-.4)/0.04)*.2*(1-Y) 2nd order explicit Runge-Kutta, CFL=1 HLLC scheme, MUSCL extrapolation, 3rd order Kim limiter Results
Ressources An example of parameter file (main.rpm): (...)
Shock reflexion in a channel which section is reduced by a 10° wedge. The upstream flow is Mach 2. One can observe (weak) shock reflexions, an expansion fan and its interaction with shock waves.
(highly refined) First order computation
The computation is fully converged to 6 orders of magnitude (local time stepping with explicit integration method). The numerical scheme is the only first order HLLC. The mesh has been automatically refined 4 times with SPLIT=ISO-TRI (...)
An unsteady shock wave (travelling Mach = 2.85) impacts a pyramid obstacle. A first reflexion occurs and then the shock is diffracted by the expansion from the spike of this pyramid. The 90 degrees corner trigger a separation.
Numerical parameters 600k quad mesh second ordre MUSCL HLLC scheme Results
This inviscid flow on a multi-element airfoil is interesting since this geometry has been defined through a conformal transformation of four cylinders. Thus, a theoretical solution can be computed.
Metis partioned mesh (4 parts)