Analytically Modeling a Dual-Mode Scramjet with Fuel Flow Rate as the Controlling Parameter

Hypersonic airbreathing propulsion has applications in defence and space accessibility. The objective of this study is to analytically model a Dual-Mode Scramjet with fuel flow rate as the controlling parameter at a design Mach number of 6 with Kerosene as fuel. The components of the scramjet were modeled individually and integrated through a one-dimensional analysis. The location of the fuel injectors determines the axial distribution of stagnation temperature in the combustor. This is necessary to evaluate the location of thermal choking. The combustor-isolator model can accommodate supersonic and subsonic combustion with the intermediate mode involving a Normal shock in the combustor. An algorithm was developed to determine the axial location of this Normal shock. On mapping the fuel flow rate to the thrust and integrating it with the Drag model, the flight profile of the vehicle can be simulated. Finally, the feasibility of controlling the trajectory (Mach number and Altitude) of a DMR-powered vehicle with the fuel flow rate as the input parameter is assessed analytically.