1. A rocket propulsion concept known as "Microwave Thermal Propulsion" consists of ground-based microwaves beamed and focused on the underbelly of a rocket to heat a propellant which is flowing through suitably positioned microwave-absorbent heat exchanger walls. The purpose of this is to heat the propellant to a stagnation temperature as high asT₀= 2500 Kwithout having to carry the source of heat. Assuming the same hardware is used so that the thrust coefficient,C_F? 1.7, applies to all propellants of interest, calculate the ideal specific impulse (I_s) for each of the cold-propellants gasses in Table 7-3: (a) Hydrogen, (b) Helium, (c) Methane, (d) Nitrogen, (e) Air, (f) Argon, and (g) Krypton. (2 Points per Part)