Numerical Analysis of a Flame Deflector Using Reactive an Non-Reactive Flow Models

Date

2026-01-01

Author

Irirolya, Tohid Ghorbani
Eyi, Sinan
Tsutsumi, Seiji

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During the ignition of solid and liquid rocket motors, ignition overpressure (IOP) wave is generated. The IOP is caused by the rapid expansion of exhaust gases, which compress the surrounding air and behaves like blast wave or shock wave. The wave propagates along the launch vehicle and structures and can cause damages to both of them. The IOP is characterized by high magnitude and low frequency. This study aims to investigate the IOP phenomenon in non-reactive flow and reactive flow through supersonic nozzle flow in a 2D configuration. Numerical simulations are conducted using a reactingPimpleCentralFoam (RPCF) solver which can handle compressible flow with combustion and chemical reactions in OpenFOAM. Numerical verification and validation of the RPCF solver have been carried out. The verification confirms the solver’s accuracy for non-reactive supersonic flows, while the validation demonstrates its ability to capture combustion and chemical reaction effects in reactive flow simulations. The effect of combustion on ignition overpressure is significant, particularly at the impinging wall and in regions near the point of impingement.

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https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=105031182333&origin=inward
https://hdl.handle.net/11511/118850

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Department of Aerospace Engineering, Conference / Seminar