|
|
Propellant
|
|
+oxidant 686 Oxygene
|
|
+fuel 673 Octane
|
|
+o/f 2.55 O/F ratio
|
|
|
|
|
|
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
|