Engineering, 13.10.2020 03:01 asdf334asdf334
You need to calculate the mass flow rate of the exhaust leaving a Trident II Intercontinental Ballistic Missile at 25000 m above sea level ( P = 2549 Pa , T = 221 K and R = 287 J/ kg K). Assume that the exhaust is air (it isn’t in real life, but air is OK here) and you have the following information: A = 3.5 m^2 , rocket V = 2700 m/s and Vexhaust = 4500 m/s.
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