Data on various liquid rocket engine propellants: ideal specific impulse as a function of mixture ratio

Classification of the propellants can be done by evaluating their characteristic velocity and thrust coefficient. Therefore, a high combustion temperature, a low isentropic exponent, as well as a low molecular weight of the exhaust gases is preferable. The physical properties of the propellants are driver for engine cycle selection and launcher design for achieving the optimal specific impulse as a performance requirement.

The repository contains data and corresponding relations of the specific impulse to fuel mixture ratios for various liquid rocket engine propellant pairs.