三维等离子体MHD气动热环境数值模拟

doi:10.7527/S1000-6893.2017.121030

Abstract

Abstract:

Electromagnetic flow control technique, a significant multidisciplinary intersecting direction, shows wide application prospects in aerodynamic characteristics optimization, aerodynamic thermal environment mitigation, boundary layer transition and plasma distribution for flow control over hypersonic vehicle. In this paper, chemical reactions, molecular vibration excitation and chemical non-equilibrium effects are considered in the flow field of hypersonic vehicle, coupled with electromagnetic field effect and with the assumption of low magnetic Reynolds number. By solving 3D chemical non-equilibrium Navier-Stokes equations and Maxwell equations, numerical simulation method and the corresponding computational codes are developed for extra magnetic field coupled with reentry plasma flow, and are validated by numerically calculating two typical examples. These simulation results are in agreement with those in literatures. On this basis, the influence of extra magnetic field on 3D plasma flows and aero-thermal environment under different flight conditions is studied. The results show that extra magnetic field can obviously change the standoff distance of shockwave and reduce the surface heat flux in most surface regions. It is found that the greater the magnetic field strength is, the more obvious the modification effect is. The influence degree is relevant to the factors of flight altitude, velocity and extra magnetic field configuration. Under current calculation conditions, the influence degree is more obvious when the flight altitude is higher.

Key words: MHD, plasma, chemical non-equilibrium, numerical simulation, aero-thermal environment

CLC Number:

DING Mingsong, JIANG Tao, DONG Weizhong, GAO Tiesuo, LIU Qingzong. Numerical simulation of 3D plasma MHD aero-thermal environment[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(8): 121030-121030.

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Numerical simulation of 3D plasma MHD aero-thermal environment

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