Multidisciplinary Analysis and Evaluation of SupersonicCombustion Ramjets

摘要

Hypersonic airbreathing propulsion systems are highly integrated systems, demanding for appropriate numerical and analytical methods for analysis and evaluation. Therefore, this paper introduces a multidisciplinary tool for the prediction of performance limits in the design phase or for reverse engineering of given supersonic combustion ramjet (scramjet) configurations. Simulation models for the individual part of a scramjet as well as methods defining and evaluating the performance limits are discussed. By means of a generic two-dimensional scramjet configuration, possibilities and limitations associated with the applied methodology are presented.