In this thesis, a model of a generic scramjet that employs boundary layer combustion of hydrogen for use in further studies into optimizing the drag reducing effects of boundary layer combustion in scramjets was developed. The modeling of the scramjet includes a Busemann biplane inlet, a Rayleigh-line model of heat addition to simulate combustion in the burner, a quasi-1D expansion in the thrust nozzle, van Driest II skin friction calculations, and an analytic model of the boundary layer combustion skin friction reduction developed by Stalker (2001) for the inlet and combustion chamber. The scramjet produced a specific impulse of 1460 s for Mach 10 flight at 30 km altitude with an equivalence ratio of 1 for fuel injection in the combustor, an inlet ramp angle of 16 degrees and expansion ramp angle of 12 degrees. The simple model of the expansion on the thrust surface over predicted the thrust for these conditions. While this will affect the overall specific impulse of the vehicle, it is not expected to influence studies into optimizing boundary layer combustion techniques. Skin friction on the inlet was reduced by approximately 60% using boundary layer combustion, compared to only 35% reduction with the film cooling effects of hydrogen injection alone. Boundary layer combustion was implemented in the combustion chamber, however the solution did not converge. This model can be used to optimize scramjet boundary layer combustion in terms of specific impulse by varying the ratio of mainstream to boundary layer fuel injection and the injection locations along the inlet and combustion chamber.