스크램제트 쐐기형 분사기의 유동 혼합 특성 LES

Mixing between air and fuel is important factor for efficient and stable combustion in scramjet engine. Therefore, numerical method which considers physical mixing mechanism is required to simulate supersonic mixing and combustion. Large eddy simulation is capable of reproducing turbulent mixing phenomenon, however application of LES for supersonic regime is being sought due to its high level of difficulty. In this study, 3-dimensional LES method for supersonic flow analysis is suggested, and simulation of supersonic combustor with wedge shaped injector is performed. As a result, complicated flow structure include shock induced by wedge and interaction between shock and boundary layer is well captured. Moreover, discontinuous contact surface of shock waves, periodic motion, and mixing characteristics of sample fuel is observed.