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A computational model is developed to assist the design of the first hybridrocket engine of the McGill Rocket Team, using liquid nitrous oxide as anoxidizer and solid paraffin wax as a fuel. The model is developed in threephases: In the first phase, a steady-state model which neglects transientperformance decrease of the hybrid engine is considered. The steady-state modelconsiders: a constant oxidizer mass flow rate; a combustion chamber in chemicalequilibrium; a one-dimensional isentropic nozzle; and a one-dimensionalconstant-thrust rocket ascent. The steady-state model is used to conductparametric studies on engine performance as a function of design parameterssuch as: oxidizer mass flow rate, fuel grain dimensions, and nozzle dimensions.The engine design point is selected to optimize specific impulse, givenphysical and structural constraints of the system. In the second phase, anunsteady model incorporating transient performance decrease of the hybridengine is considered. The transient model considers: a self-pressurizingoxidizer tank in quasi-steady liquid-vapor equilibrium; a combustion chamber inquasi-steady chemical equilibrium; a one-dimensional non-isentropic nozzle; anda one-dimensional rocket ascent model. The transient performance profile of theengine is established, and the unsteady model is used to predict propellantrequirements for the launch vehicle, given a target apogee of 3048 m (10,000ft). In the third stage, the unsteady model is compared to hot fire testingdata of the McGill Rocket Team. Semi-empirical parameters used in theformulation are calibrated against testing data, and the validity of the modelis assessed.

A computational model for the design of a nitrous oxide--paraffin wax hybrid rocket engine