Numerical simulation of 3D plasma MHD aero-thermal environment

被引：0
|
作者：
Ding M. [1 ]
Jiang T. [1 ]
Dong W. [1 ]
Gao T. [1 ]
Liu Q. [1 ]
机构：
[1] Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang
来源：
Ding, Mingsong (dingms2008@qq.com) | 1600年 / Chinese Society of Astronautics卷 / 38期
关键词：
Aero-thermal environment; Chemical non-equilibrium; MHD; Numerical simulation; Plasma;
D O I：
10.7527/S1000-6893.2017.121030
中图分类号：
学科分类号：
摘要：
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. © 2017, Press of Chinese Journal of Aeronautics. All right reserved.
引用
收藏
相关论文
共 22 条
  • [1] Le J.L., Reentry Physics, pp. 9-21, (2005)
  • [2] Maccormack R.W., Evaluation of the low magnetic Reynolds approximation for aerodynamic flow calculations, (2005)
  • [3] Lee J., Huerta M.A., Zha G.C., Low Re<sub>m</sub> 3D MHD hypersonic equilibrium flow using high order WENO schemes, (2010)
  • [4] Bisek N.J., Poggie J., Exploration of MHD flow control for a hypersonic blunt elliptic cone with an impregnated ablator, (2011)
  • [5] Chernyshev A., Kurakin Y., Schmidt A., Effect of MHD system arrangement on high speed plasma flow structure around conical body, (2012)
  • [6] Fujino T., Ishikawa M., Numerical simulation of MHD flow control along super orbital reentry trajectory, (2013)
  • [7] Takahashi T., Shimosawa Y., Masuda K., Et al., Numerical study of thermal protection using magneto-hydrodynamic flow control in mars entry flight, (2015)
  • [8] Masuda K., Shimosawa Y., Fujino T., Three-dimensional numerical simulation of magnetohydrodynamic flow control in reentry flight, (2015)
  • [9] He X., Chen J.Q., Deng X.G., NND scheme's application in multi-dimensional ideal magnetohydrodynamic equations, Acta Aerodynamica Sinica, 23, 3, pp. 267-273, (2005)
  • [10] Pan Y., Numerical methods for hypersonic flowfield with magnetic interference, (2007)
123