Design and Optimization of a Small Scale M=8 Scramjet Propulsion System

Abstract

One of the major objectives of the EC-co funded research project LAPCAT II is demonstrating positive aero-propulsive balance of a scramjet propelled vehicle in a wind tunnel. For this, the LAPCAT MR2.4 hypersonic cruiser needed to be scaled to lab scale. An optimization of the internal flow path was necessary, to cope with the slightly different flight conditions and constraints in the laboratory environment. Therefore, a study featuring reactive CFD simulations using the TAU solver was carried out. It was found that the best way to achieve a high combustion efficiency is to use a staged injection scheme in the combustor. The results were verified with nose-to-tail simulations of the small-scale configuration under wind tunnel conditions, showing that positive net thrust can be expected from the experimental campaigns.