Write a program (in MATLAB, Excel, or similar) that wll locate the normal shock in a nozzle given the inlet and outlet pressures and the nozzle geometry. The location of a normal shock can be determined as follows. Mass conservation in a nozzle implies that that poA* is constant Further, the stagnation pressure after the shock can be related to the exit pressure and exit Mach number. From these, we can show that the following relation must be true: where subscript 1 denotes properties before the shock, subscript 2 denotes properties after the shock, and subscript e denotes exit properties. This equation allows the exit Mach number Me to be calculated from the input parameters, if the exit pressure is consistent with isentropic nozzle flow with a normal shock. Under-expanded or over-expanded nozzles cannot be solved using this approach. Given Me, the stagnation pressure at the outlet can be calculated and compared to the inlet pressure. This ratio specifies the inlet Mach number of the normal shock. The inlet Mach number of the normal shock dictates A/A at the point of the normal shock, and thus the location of the normal shock With this program, determine the location of a normal shock for a nozzle with cross-sectional area specified by A 725-100x for 0