2. You have been asked to do a preliminary design of a rocket engine with the following attributes:

The fuel is CH4 and O2 is the oxidizer with a required sea-level thrust of 2.34 MN

The overall O/F (mass) ratio is 3.3 The operating pressure for main combustion chamber is around 160 atm

The adiabatic flame temperature in the main combustion chamber is around 3660 K

The nozzle expansion ratio is 30.0 and the divergence correction is 0.985

Estimate the following parameters without assuming calorically perfect (i.e., use equilibrium software +) to calculate the nozzle performance. If you approximate make sure to note this.

(a) The equilibrium composition in terms of mole fraction

(b) The exit velocity ue of the nozzle assuming the flow in it is in equilibrium

(c) The mass flow rates for the fuel mf and for the oxidizer mox at sea level

(d) The nozzle throat diameter (assume a circular cross-section), Dt

(e) The specific impulse Isp of the engine at both sea-level (sl) and in vacuum (vac)