Is it safe to assume a mixture ratio of 2.16 with an ISP of 313 s for the NTO/MMH, SuperDraco Engine manufactured by SpaceX?
I am referencing the 2.16 propellant mixture ratio, and estimating or more so assuming the ISP.
I am calculating the propellant mass required for NTO/MMH propellant rocket engine, SuperDraco to conduct a change of Delta-V. However the calculation relies on mixture ratio of the propellant and ISP of the rocket engine? Can I please get your input for more accurate values. [http://www.astronautix.com/n/n2o4mmh.html ]