Quasi-1D Aero-Thermodynamic Flowpath Modeling of an Inversely Designed Morphing Hypersonic Engine Vol 1

Encouraged with the successful testing of the X-51A/SCRAMjet Engine Demonstrator concept, there continues to be interest in the development of the Dual-Mode scramjet as a promising high-speed air-breathing hypersonic engine. In contributing to that effort the work described herein builds on the authors previous works on this subject area. Focus in this paper is on the development of a quasi 1D model which will be used to; (1) attempt to validate the performance of the morphing dual mode scramjet, and (2) used as a base for the development of models of greater complexity. Initially the geometric and aerodynamic models for the forebody section of the morphing hypersonic engine are developed using an inverse design approach. For this particular design phase a total of three inputs (freestream velocity, wedge angle and wedge length) are used to generate the appropriate geometric and aerodynamic models. Next information obtained from the forebody section is used in the development of the quasi 1D model for the combustor-nozzle section of the morphing scramjet engine. The quasi 1D combustion model is developed using four fuels. These fuel are (1) a propane-methane mixture, (2) a propane-hydrogen mixture, (3) a methane-hydrogen mixture, and (4) a hydrogen fuel.