All chemical propulsion systems, and some electric propulsion systems, rely on heat addition from either chemical reactions or heat transfer from an external source. We saw in class that heat addition to a subsonic flow increases the Mach number, and that heat addition to supersonic flow decreases the Mach number. In either flow, heat addition results in a loss of stagnation pressure and moves the flow toward M = 1.0. Let's look at the effects of Mand Q closer. a) Flow entering a ramjet combustor has properties M = 0.25, p = 50 kPa, and T = 400 K. It is heated to an exit temperature of To= 1400 K. Use the Rayleigh flow table in the Handouts folder in Brightspace to determine the properties M, T, u, p, and po at the exit of the combustor. Also determine the amount of heat q* that would thermally choke the flow. Let cp = 1.0 kJ/kg-K and y= 1.4. b) What rate of heat addition would be required to decelerate 2 kg/s of H flowing at M = 2.0 to M = 1.0 if the initial temperature of the H is T = 600 K? Let cp = 14.5 kJ/kg-K and y= 1.4.