Dynamic Computational Analyses of Complete Scramjet Engine Modules.

摘要

The research performed during this period has produced and demonstrated all of the required codes, algorithms and technology needed to analyze dynamically scramjet propulsion modules, both singly and ganged. Cold- flow unstart of a generic hydrocarbon-fuel configuration (tested at NASA langley) due to nozzle backpressure and angle of attack change have been obtained and animated for analysis. An inlet isolator combuster hydrogen fueled configuration tested at the National Aerospace Laboratory in Japan has been simulated synamically and analysed to determine the cause of flow path destabililzation. Finally, an algorithm to allow dynamic adaptation of adjacent blocks has been developed to allow resolution of all of the physics while maintaining conservation between blocks. The codes have not yet been integrated. Follow-on funding will be sought to do so.