A coverging$-$diverging nozzle is supplied by a huge air reservoir. The nozzle has a throat area of $10$ cm$2$ and an exit area of $20$ cm$^2.$ The reservoir$$s static pressure and temperature state is $300$ kPa$($abs$)$ and $30$C$.$ Determine the range of back pressures $($pressures measured just beyond the exit plane of the nozzle$)$ over which oblique shocks form beyond the nozzle$$s exit plane. Also, where shocks appear inside the nozzle.