LES of Reacting Flow in a Hydrogen Jet into Supersonic Crossflow Combustor Using a New Turbulent Combustion Model

Modelling the complete flow physics and chemical kinetics of supersonic combustion is a particularly complex daunting task that requires significant computational resources. To foster performance evaluation tools for future hypersonic vehicles, developing accurate yet computationally efficient solution methods great importance. In this work, new subgrid model large eddy simulations derived used in three-dimensional in-house solver to provide experimental scramjet ground tests. particular, paper introduces hybrid closure with reaction-rate approach close filtered source terms governing equations species mass fractions total energy. The developed here makes use linear bridging function, depending on segregation rate mixture fraction, between resolved contribution issued from perfectly stirred reactor (PSR) estimation, subgrid-scale (SGS) where approximates Lagrangian trajectory composition space retained. considers effect fluctuations compositions can be extended take into account, example, temperature. tested using hydrogen-fueled combustor circular injector Mach 2 vitiated airflow pressure temperature 0.40 MPa 1695 K, respectively. selected operating conditions are representative LAPCAT-II dual-mode ramjet/scramjet combustion. Chemistry described four-step reduced mechanism. results obtained present modelling proposal compared those numerical performed quasi-laminar chemistry or PSR approach. These do show that, even highly mesh, effects remain significant, especially vicinity injection SGS scalar field non-negligible.