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