# Liquid rocket engine excercise

• mirko9670
mirko9670
Homework Statement
Find thrust and specific impulse
Relevant Equations
How can i derive the thrust? i am missing some parameters
I know it is an homework excercise but I already tried all the isoentropic relations, the problem is not the Isp, I can't find a relation to calculate the thrust as I am missing some important parameters, such as Ae, At, mdot, and thrust. This is the text of the excercise:

A bipropellant rocket engine is required for Mars landing. It will be the main engine driving the soft landing of a capsule on the martian soil to carry a scientific payload. The ground environment where the lander will operate is characterized by the following properties: Temperature: -60°C Pressure: 610 Pa Composition: mainly CO2 Acceleration due to gravity force: 3.7 m/s2

Show the formula and compute the thrust and the specific impulse for this propulsion unit if the following properties are obtained. (Assume isentropic expansion) Chamber pressure: Pc = 15 bar Exit-to-chamber nozzle pressure ratio: OPTIMAL EXPANSION Nozzle exit velocity: Ve = 2450 m/s Specific heat ratio: 1.3 Molar mass of exhaust gases: 24 g/mol

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