亚声速电磁橇逆向合成射流气动减阻分析--流动控制与热管理

doi:10.7527/S1000-6893.2026.33491

Abstract

Abstract: To address the challenge of time-varying aerodynamic drag during the operation of electromagnetic launchers, an active flow control drag reduction method based on piston-type synthetic jets is proposed. The accuracy of the simulation method in this paper is verified through hot-wire anemometry experiments and full-scale sled-track coupling model experiments. The influence laws of the driving frequency of the jet actuator, the velocity distribution characteristics of the jet, and the reverse jet on the flow field characteristics of the windward surface of the sled magnet are systematically studied. The research results show that the peak velocity of the piston-type synthetic jet and the driving frequency exhibit significant nonlinear evolution characteristics, and the velocity characteristics can be accurately characterized by cubic polynomial fitting. Under a 0.5Ma incoming flow condition, the flow field topology is reconstructed through the unsteady interaction between the synthetic jet and the incoming flow, generating a vortex ring at the leading edge of the blunt body and forming an equivalent virtual deflector shape, which effectively suppresses the high-pressure accumulation on the windward surface of the sled magnet and reduces the pressure difference drag. Numerical simulations also reveal that the drag reduction effect of synchronous jets is significantly affected by the jet intensity and its spatial gradient, and asynchronous reverse jets can effectively suppress the large fluctuations in drag caused by synchronous jets.

Key words: Synthetic jet, Electromagnetic sled, Reverse jet, Vortex ring evolution, Equivalent virtual shape, Aerodynamic drag reduction

CLC Number:

References

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Aerodynamic drag reduction analysis of subsonic electromagnetic sled with reverse synthetic jet

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