Air at $2.5 \mathrm{kPa}, 221 \mathrm{~K}$ approaches the intake of a ramjet engine operating at an altitude of $25 \mathrm{~km}$. The Mach number is 3.0. For this Mach number, a normal shock stands just ahead of the intake. Determine the stagnation pressure, static pressure, and temperature of the air immediately after the normal shock. Also, calculate the percent loss in stagnation pressure. Repeat the calculations for Mach number equal to 4. The high loss of stagnation pressure that you see from your calculations illustrates why the intake of a ramjet has to be designed carefully to avoid such normal shocks during operation.