[saisanthoshm88]

I was trying out a ANSYS CFX workshop - Transonic flow over a NACA 0012 Airfoil and the Mach number used in the workshop was 0.7. Everything went well when the same Mach number was used but while running the simulation for higher mach numbers it was found that the solver is struggling more to reach the convergence target (= 1E-6 R.M.S). The Reynolds number is 9e6.The SST turbulence model is used. Dynamic viscosity is 1.82e-5. The temperature for the simulation is 288 K. The image attached shows the calculations for the pressure ( which is applied at the outlet boundary) and the velocity ( which is applied at the inlet boundary). Can some one suggest the ways by which I can have a more smoother convergence trend at Mach numbers higher than 0.7 in this problem.