Hai FENG, Tai JIN, Kun WU

DOI Number: N/A

Conference number: HiSST-2024-328

Thermodynamic non-equilibrium effect has a significant impact on hypersonic aircraft and must be taken into consideration in numerical computations. Numerical simulations of a Mach 12 flight condition scramjet engine were conducted using both thermodynamic equilibrium models and Park’s dual-temperature non-equilibrium model. The results indicate that, compared to equilibrium state calculations, non-equilibrium effects lead to a rearward shift in the wave system position, resulting in a noticeable reduction in peak pressure between shock waves, with a more pronounced impact on the reaction flow. The non-equilibrium Ttr temperature field is generally similar to the equilibrium state. Thermodynamic non-equilibrium effects lead to a slight reduction in Ttr. In the non-equilibrium state, the combustion efficiency at the outlet section of the combustion chamber is higher, indicating that thermodynamic non-equilibrium effects enhance the extent of the reaction.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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