4. A single-stage rocket with total initial weight of 20,000 kg and specific impulse of 350...

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4. A single-stage rocket with total initial weight of 20,000 kg and specific impulse of 350 s has combustion chamber conditions of 100 bar and 2500 K with a throat diameter of 0.3 m. a. For a vertical launch trajectory, plot the vehicle velocity and propulsive efficiency as function of time until burnout. Assume the propellant mass ratio (of total mass) is 0.9. b. If the propellants are methane and oxygen (in stoichiometric balance) that are fully converted to combustion products, calculate the internal efficiency and total rocket efficiency as function of time (plot along with the propulsive efficiency). Assume c* efficiency is 1.0. Assume average molecular weight exiting the rocket is 24 g/mol and y = 1.3. (Please note: when using tables, gmol and mol are the same) 4. A single-stage rocket with total initial weight of 20,000 kg and specific impulse of 350 s has combustion chamber conditions of 100 bar and 2500 K with a throat diameter of 0.3 m. a. For a vertical launch trajectory, plot the vehicle velocity and propulsive efficiency as function of time until burnout. Assume the propellant mass ratio (of total mass) is 0.9. b. If the propellants are methane and oxygen (in stoichiometric balance) that are fully converted to combustion products, calculate the internal efficiency and total rocket efficiency as function of time (plot along with the propulsive efficiency). Assume c* efficiency is 1.0. Assume average molecular weight exiting the rocket is 24 g/mol and y = 1.3. (Please note: when using tables, gmol and mol are the same)