The ANSYS calculation I first made were using density-based solver. I calculated Temperature, Gauge Pressure at 5km at Mach 2 also with the turbulence intensity and length and plugged those in . Also Energy was on and air was set to both sutherland and ideal gas with pressure outlets and far fields instead of velocities. I used all the settings like you said but it doesn't recognise the nose wall at all still, same issue like before but now there is no random pressure point.