An airplane diffuser as shown below, has a normal shock attached to the edge of the diffuser when the plane is flying at a certain mach number. If at the exit of the diffuser, the mach number is $0\mathrm{.}3,$ what must be the flight mach number. The inlet area is $0\mathrm{.}29$ m$^2$ and exit area is $0\mathrm{.}44$ m$^2$