You are asked to develop a nozzle for a Mars lander propulsion system. The maximum landing mass of the vehicle is 1000 Kg and the chamber pressure for the engine is 1.0 MPa.The propellants deliver a C* of 1500 m/s at1.2 with18 Kg/Kg-mol . Assuming The thrust just balances the max vehicle weight at landing, determine:a) The maximum expansion ratio which can be used to avoid flow separation.b) The throat and exit diameters of the nozzle.The ambient pressure and temperature on the system of Mars are 2 KPa and 220K,respectively and the gravitational acceleration is 38% of Earth's