Info

Notes:

Combustion chamber pressure—1000 psia (6895 kN/m2); nozzle exit pressure—14.7 psia (1 atm): optimum expansion. Adiabatic combustion and isentropic expansion of ideal gas

The specific gravity at the boiling point was used for those oxidizers or fuels that boil below 20°C at 1 atm pressure. Mixture ratios are for approximate maximum value of Is.

Notes:

Combustion chamber pressure—1000 psia (6895 kN/m2); nozzle exit pressure—14.7 psia (1 atm): optimum expansion. Adiabatic combustion and isentropic expansion of ideal gas

The specific gravity at the boiling point was used for those oxidizers or fuels that boil below 20°C at 1 atm pressure. Mixture ratios are for approximate maximum value of Is.

TABLE 5-6. Theoretical Performance of Typical Solid Rocket Propellant Combinations

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