Numerical Simulation For Hypersonic Flowfield With Electromagnetic Interference

With the development of MHD(Magnetohydrodynamic) flow control technology, its applicationin the field of hypersonic has became the new focus of research. This dissertation combines thediscipline of computational fluid dynamics, electromagnetics and plasma dynamics. The numericalmethods are developed for hypersonic MHD flow field, and a plasma generation model is establishedbased on electron beam induced ionization. Finally, the MHD control technology for hypersonic flowbased on electron beam induced ionization’s plasma generation model is developed. The calculationcodes are developed using these models.Firstly, the basic theory and relationship of MHD and plasma dynamics are studied to establishthe theoretical basis for further numerical simulation. The MHD equations are derived from the basicequations of Hydrodynamics and Electromagnetics, along with the basic assumptions ofmagnetohydrodynamics; the plasma particle number, momentum and energy conservation equationsare derived from the plasma kinetic equation. Finaly, the plasma’s mobility-diffusion model is derivedfrom the conservation equations of plasma assisted to the equilibrium fundamental properties andtransport diffusion relationship of the plasma.Numerical methods for the hypersonic MHD flowfield were investigated. Based on the blockstructure finite volume method and OpenMP parallel strategy, an efficient numerical method isdeveloped, using an implicit LU-SGS time-marching, second-order spatial discretization andturbulence model. S-A one-equation turbulence model, k two-equation turbulence model andSST two-equation turbulence model are implemented to evaluate the turbulence viscosity. In thisdissertation, three flux splitting schemes are implemented to calculate the fluxes of full MHDequations:1) the first scheme is AUSM(Advection Upstream Splitting Method), which has beenmodified for the multidimensional ideal full MHD equations;2) The second shceme which is basedon the original HLLC flux-splitting scheme, is implemented to calculate the fluxes ofmultidimensional ideal full MHD by modifying the calculation method of intermediate variables andadding new restrictions to ensure the conservation of calculation format;3) The last scheme whichwas developed by MacCormack based on the restoration of homogeneity of MHD equations, isapplied to calculate the fluxes of multidimensional ideal full MHD equations, using the splittingmethod of Van Leer. Numerical methods of divergence cleaning for the hypersonic MHD flowfeildwas investigated. In this dissertation, the projection method and hyperbolic divergence cleaningmethod are implemented to get rid of the influence of divergence caused by the erro of numerical simulation. The results indicate that the numerical simulation method has good robustness andresolution.In this dissertation, a new plasma generation model based on the electron-beam model and thethree-component plasma mobility-diffusion model is established to apply MHD control technology tothe real hypersonic flowfeild. And then the low magnetic Reynolds number MHD-electron beaminduced ionization plasma model’s control equations are derived by modifying the original lowmagnetic Reynolds number MHD equations. The numerical simulation codes are developed usingthese control equations. The results show that the MHD flow control technology based on the plasmageneration of electron-beam-induced ionization can improve the performance of hypersonic vehicle.