Simulation of hypersonic flow within electromagnetic fields [electronic resource]
- Jun Kyu Lee.
- Physical description
- 1 online resource.
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|3781 2015 L||In-library use|
- Lee, Jun Kyu.
- Cantwell, Brian, primary advisor.
- MacCormack, R. W. (Robert William), 1940- primary advisor.
- Alonso, Juan José, 1968- advisor.
- Stanford University. Department of Aeronautics and Astronautics.
- Space vehicles that enter the atmosphere require the use of a Thermal Protection System (TPS) to protect them from aerodynamic heating. The TPS currently in use is composed of a heat-resistant material to protect the inner part of the vehicle, and it adds tremendously to the cost of a space mission. In contrast, it has been pointed out that such a high enthalpy gas flow, which is partially ionized, could be controlled through an electromagnetic effect, and as a result, the high convective heat could be reduced, and furthermore, the aerodynamic force acting on the vehicle could be controlled. A lot of research has been carried out, not only theoretically but also experimentally, to understand the electromagnetic effect. However, numerical accuracy in predicting these effects, especially for heat flux mitigation, has not been satisfactory. Accurate simulation of such flows requires the solution of the Navier-Stokes equations for compressible viscous flow, and for the equations describing the state of the high temperature gas containing many species in chemical and thermal equilibrium or non-equilibrium. In addition, Maxwell's equations for including the effects of electromagnetic fields upon an ionized hypersonic flow through Lorentz forces and Joule heating need to be solved in order to realize flow control advantages. Inclusion of these three sets of equations in the numerical simulation of hypersonic flow is computationally intensive and stiff to solve. Therefore, many researchers have made a number of simplifications based on certain assumptions to reduce the size of the governing equations. However, these simplifications and assumptions are not valid under certain flight regimes and can lead to inaccurate estimates of heat flux to the vehicle. In this thesis, the full magneto fluid dynamics (MFD) equations, including multi-species, chemical reactions, and Maxwell's equations, have been solved. The approach includes formulation of the full governing equations, the boundary conditions including catalytic, cold wall boundaries, and the numerical procedure for solving the governing equations. The solver is verified and validated with experimental data provided by Ziemer for shock stand-off distance, by Gulhan et al. and Kawamura et al. for heat flux mitigation. The numerical results show an excellent match with previously published experimental data.
- Publication date
- Submitted to the Department of Aeronautics and Astronautics.
- Thesis (Ph.D.)--Stanford University, 2015.
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