SCCREAM v.5: A Web-Based Airbreathing Propulsion Analysis Tool

Abstract

To properly assess the advantages and disadvantages of various RBCC design options at the conceptual vehicle level, an engine performance analysis tool is required. This tool must be capable of modeling engine performance effects that will subsequently be propagated throughout the conceptual design process via trajectory analysis, weight assessment, fuel balance calculations, thermal environment, life cycle cost, etc. For a given engine configuration, the tool will need to generate engine thrust and Isp as a function of altitude and Mach number for each operating mode of an RBCC engine. A project to create a new computer program for the analysis of RBCC engines has already been initiated. Called SCCREAM, for Simulated Combined-Cycle Rocket Engine Analysis Module, it is intended for use in the conceptual phase of airbreathing launch vehicle design. This paper will detail the capabilities of the latest version of SCCREAM and present the results of validation efforts. Combustor thermodynamic properties and overall engine performance for a sample engine will be compared with industry standard codes. Results from the new scram-rocket mode will be discussed. Ejector mode performance plots generated over the web will also be presented.