I try to make a hybrid rocket engine which impuls is almost 3200-3500N.I consider to use paraffın for fuel and oxyjen for oxider.What is leght of the motor probabably? and How can I calculate nozzle design and amount of gas?
Regardless of which propellant you use, we will not discuss propellant formulas on the open forum. That is reserved for the research forum which is restricted to US citizens who have a minimum of L1 HP certification by NAR or TRA.
