A Multi-fidelity Simulation Method for Hypersonic Airbreathing Propulsion System

Jun Liu, Huacheng Yuan, Jinsheng Zhang, Zheng Kuang

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-436

As the hypersonic vehicle is highly integrated, a multi-fidelity simulation method based on commercial
solver is developed to save the simulation time for this vehicle and its propulsion system. This method
is characterized with high-level fidelity numerical analysis of external flow and low-level fidelity
numerical analysis of internal flow. The external flow of propulsion system are solved by RANS equations.
The internal flow is modeled by quasi-one dimensional equation. The interaction between external and
interflow is governed by the CFD solver through user-defined function. The static pressure distribution
acquired from multi-fidelity simulation method agrees well with the experimental data, indicating that
this simulation method can be used to study the flow physics in hypersonic propulsion system at a
reasonable cost. The results from design point indicate that the horizontal force increases with fuel
equivalence ratio and the thrust balance is realized at φ=0.35. The positive net thrust is maintained
throughout the flight regime from Ma 4 to Ma7 whether the combustor operates in ramjet or scramjet
mode.

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external and internal flow, hypersonic air-breathing propulsion system, multi-fidelity simulation method, quasi-one dimensional model

In Categories: HiSST 2022, Propulsion Systems and Components

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