The design and performance analysis of the scramjet engine flow path is inseparable from the accurate simulation of the combustion flow field. In this study, the FPV (Flamelet/Progress Variable) combustion model was employed for scramjet engine simulation, and its results were analyzed and compared with the simulation results obtained with Partially Stirred Reactor (PaSR) combustion model. A FPV model-based solver, which is named FPVFoam, was developed under the OpenFOAM platform. Then comparative investigations between the established solver FPVFoam in this study and the original solver rhoReactingFoam which uses PaSR combustion model, were carried out for the DLR strut scramjet engine. The results showed that compared to the rhoReactingFoam, the established FPVFoam solver in this study could accurately capture the local combustion quenching phenomenon in the combustion flow field and the computational efficiency could be improved by as high as 43.9% due to the decoupling of the flow and combustion calculation in FPV model. However, as the compressible characteristics of the supersonic flows was not considered in the FPV model, simulation errors to the experimental data were still generated, and the modifications accounting for compressibility effects and other high-speed flow characteristics should be considered for scramjet engine simulation application.
Yang et al. (Wed,) studied this question.