A rocket using hydrogen-oxygen as the fuel-oxidizer combination has a specific impulse of 360s. Calculate the ratio of propellant mass to initial mass required to achieve a burnout velocity equal to the escape velocity from Earth (11.19 km/s). Use the values on the table.

 

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Average Molecular Fuel-Oxidizer Combination Adiabatic Flame Weight of Combus- Temperature, K Kerosene-oxygen 3144 Hydrogen-oxygen 3517 Hydrogen-fluorine 4756 tion Products Isp, S 22 260 240 16 360 10 390 Average Molecular Fuel-Oxidizer Combination Adiabatic Flame Weight of Combus- Temperature, K Kerosene-oxygen 3144 Hydrogen-oxygen 3517 Hydrogen-fluorine 4756 tion Products Isp, S 22 260 240 16 360 10 390