[ankur bhatangar]

Hey everyone, I am trying to simulate flow over radome using Ansys fluent at Mach 4. Flow domain consist of radome with missile some portion attached to it.. Computational domain consist of cylindrical wall all around as farfield and inlet as farfield and pressure outlet...basically the missile part is fixed to the pressure outlet as shown in figure... The grid consist of unstructured mesh all around with prism layer over radome and missile portion... Everytime I am starting the simulation it's getting unstable and showing #NAN's ... Same mesh is working at low Mach number value 2.5. I am using density based solver with SA turbulence model ..Can anyone explain me what is the problem with simulation ? How can i use the same grid for all Mach number regimes provided range from subsonic to high supersonic..??..

Thanks..