2. A spacecraft with a circular cross section (diameter 3.9 m) normal to its path on atmospheric reentry encounters a condition of Mach 4 at 14,000 m altitude. A normal shock precedes the vehicle path. If simplifying assumptions can be made about the pressure in the back of the vehicle as being equal to the ambient pressure and the front face of the spacecraft experiencing the stagnation pressure after the shock with no wall shear stress calculate the force (in Newtons) experienced by the spacecraft due to the pressure difference and the temperature experienced at the front reentry face due to stagnation (note that the temperature at this point in the flight is significantly lower than peak temperatures experienced on initial reentry). 14,000 m 1= -56.5. ( 7 216.5K P= 14.17 kPa M = 4,0 T- 909. 3 k Por = 2151. 5 KPa Prob Toss shock 39 - Poy = 298.53 lPG Park = 14.17 A / Poy - P #) = F 3.3RX MN Py = 262 his F = 428, 320 #N