Abstract A numerical study of the ground testing of a hydrogen-fueled scramjet engine was undertaken using the commercial computational-fluid-dynamics code CFD++. The simulated Mach number was 12. A 7-species, 9-reaction-step hydrogen-air chemistry kinetics system was adopted for the Reynolds-averaged Navier–Stokes simulation. The two-equation SST turbulence model, which takes into account the wall functions, was used to handle the turbulence-chemistry interactions. The results were validated by experimentally measuring the wall pressure distribution, and the values obtained proved to be in good agreement. The flow pattern at non-reaction/reaction is presented, as are the results of analyzing the supersonic premix/non-premix flame structure, the reaction heat release distribution in different modes, and the change in the equivalence ratio. In this study, we realize the working mode of a hypervelocity engine and provide some suggestions for the combustion organization of the engine as well as offer insight into the potential for exploiting the processes of combustion and flow.
Highlights A scramjet engine ground test at Mach 12 with all components is simulated. The characteristics of the angled injector on flow field and reaction are clarified. The movement of reaction region is distinguished by changing equivalence ratio. Heat release of different combustion modes and velocity is compared quantitatively.
Numerical investigation of combustion field of hypervelocity scramjet engine
Acta Astronautica ; 129 ; 357-366
2016-09-14
10 pages
Article (Journal)
Electronic Resource
English
Numerical investigation of combustion field of hypervelocity scramjet engine
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