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- Propellant
- +oxidant 686 Oxygene
- +fuel 673 Octane
- +o/f 2.55 O/F ratio
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- Parameter
- +chamber_pressure 500 psi The chamber pressure
- +thrust 30000 N The thrust we are looking for
- +L* 45 in The characteristic chamber length
- +Dc/Dt 2.34 Chamber diameter / Throat diameter
- +theta 20 deg Convergent half angle
- +r_rt 1.5
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