Calculation of specific impulse of propellant

The function of rocket propellant is based on specific impulse which measures the kinetic energy producing ability of the propellant. The specific impulse  can be calculated from the following equation,                          

Where,

γ = Ratio of specific heat at stable pressure to specific heat at constant volume.

T_c = Combustion chamber temperature.

M=Average atomic mass of exhaust products.

P_e=External pressure

P_c = Chamber pressure, and

R = Gas constant

The above equation shows that the conditions favoring high specific impulse are high chamber temperature and pressure, low atomic mass of exhaust products and low external pressure. 

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