The Design of Scramjet Configurations for Optimal Operational Temperature and Overall Propulsion Efficiency.

摘要

The objective of this research effort were to inversely develop and analyze scramjet configurations at selected design points along the engines expected flight corridor. Once developed, the technical goals were to identify the scramjet design parameters, and evaluate their relationship relative to the scramjet overall performance. In efforts to accomplish these goals, a quasi-one-dimensional flow field solver with capabilities of modeling the real-world effects pertinent to scramjets operations was developed. 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' are of importance. Technical efforts were geared towards evaluating the performance of this new class of scramjets with existing scramjet models, report on any new findings and suggest recommendations for possible improvements to existing designs.;In this effort, star-shaped scramjet configurations with morphing capabilities were inversely carved from 2D planar flow fields. The preliminary outcomes of this research can be classified into the following two categories. First, the propulsion system design and assembly process led to the discovery of engineering parameters that directly influence the aerodynamic performance of the resulting configuration. These parameters were manipulated to generate configurations with superior thrust and Isp characteristics. Second, the design information needed to develop routines for a follow-on optimized 'ramjet-to-scramjet configuration' were generated.