Perform preliminary sizing calculations for a two stage liquid prepellant launch vehicle to lift $10\mathrm{.}000$ kg payload to GTO. Propellant is CH$4$ and LOX. $($Assume or calculate required mission velocity. Choose appropriate combustion parameters and calculate average effective exhaust velocity for each stage, calculate MR for each stage, estimate a payload mass ratio from historical data. Calculate total propellant mass, fuel mass, oxidizer mass. Calculate tank volume and propose preliminary sizing for tanks $($do not forget expulsion efficiency and ullage requirements$).$