The inverse design of thermodynamic optimized scramjets

A literature survey, conducted as part of this research effort, revealed that the scramjet is an attractive alternative to rocket engines as an alternative for access to space vehicles. The scramjet has many attractive engineering characteristics and is worthy of a realsitic engineering evaluation. The objective of this effort is to inversely derived scramjet configurations at selected design points along the engines flight corridor. In addition, the proposed design process allows for the derivation of realistic scramjet geometries by incorporating real-world effects into the design process. Once constructed, the goal is to identify the scramjet design parametrs and evaluate their relationship to the scramjet overall performance. In accomplishing this goal, a quasi-one-dimensional flow field solver with capabilities of modeling the real-world effects was developed. The quasi-one-dimensional flow field solver is based on the Runge-Kutta 4^th order scheme for solving systems of differential equations. In principle, the solver allows for the flow field evaluation within arbitrary shaped ducts in which the influences of ‘area change’, ‘friction’, ‘heating’ and ‘chemistry’ may be of importance. Plans are to conduct overall scramjet configuration performance evaluation in the Mach number range of 4 through 15. In addition, plans are underway to compare the performance of this new class of scramjets with existing scramjet models, report on any new findings and suggest recommendations possible future improvements.