Quasi-one-dimensional modeling of hydrogen fuelled scramjet combustors

Abstract

A computationally efficient, quasi-one-dimensional supersonic combustion ramjet propulsion model has been produced for use in hypersonic system design studies. The model uses a series of ordinary differential equations, solved using a 4th order Runge-Kutta method, to describe the gas dynamics within the scramjet duct. Additional models for skin friction and wall heat transfer are also included. The equations were derived assuming an open thermodynamic system with equilibrium or simplified chemistry combustion models. The combustion was also assumed to be mixing rather than kinetically limited. This assumption allows simplification of the modeling and was found to be justified when the model was compared against experimental results. Three test cases are used to validate the performance of the scramjet propulsion model: (1) modeling a reflected shock tunnel hydrogen fuelled scramjet experiment, (2) a continuous flow hydrogen fuelled scramjet ground test and (3) a segment of the HyShot II flight test.