Combustion in a Rocket Motor

If the combustion products of a propellant attain a state of thermal equilibrium, the combustion temperature may be determined theoretically, as described in Chapter 2. However, the combustion in a rocket motor is incomplete and so the flame temperature remains below the adiabatic flame temperature.bl If one assumes that the flame temperature, T, varies with pressure, p, in a rocket motor, T is expressed byl5]... 

Fig. 13.19 Pressure-time curves of stable and unstable combustion in a rocket motor.

Although propellant chemistry research concerns itself with everything from the synthesis and characterization of new molecules to their formulation and combustion in a rocket motor or engine, advanced propellant chemistry is primarily directed towards the search for new oxidizers. This intense effort is dictated by the greater contribution to energy which can be made by a small improvement here since the oxidizer normally comprises 70-80% by weight of the propellant combination. A semitheoretical approach to the ultimate energy achievable in propellants is presented. 

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