Based on the original Rocket Workbench on SourceForge in CVS at:
https://sourceforge.net/projects/rocketworkbench
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14 lines
403 B
14 lines
403 B
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Propellant
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+oxidant 686 Oxygene
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+fuel 673 Octane
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+o/f 2.55 O/F ratio
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Parameter
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+chamber_pressure 500 psi The chamber pressure
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+thrust 30000 N The thrust we are looking for
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+L* 45 in The characteristic chamber length
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+Dc/Dt 2.34 Chamber diameter / Throat diameter
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+theta 20 deg Convergent half angle
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+r_rt 1.5
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