consider a hypersonic missile flying at mach 8 at an altitude of 6 km. the nose of the missile is blunt. calculate the pressure at the stagnation point on the nose. 2·(20 pts) show that the thermodynamic quantities across a shock can be related as e2-e1 = hint: the continuity, momentum, and energy equations across a normal shock wave are (v1-v2) . 2 2 3 - (20 pts) ergent-divergent nozzle with an exit-to-throat area ratio of 1.616 has exit and reservoir pressure atm reenectively in addition, the reservoir temperature is 288 k and the throat are equal to 0947 and 1 0 reg