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• W2313564936 abstract "In this paper, a three-dimensional flow solver (BGK-NS3D), which is based on the gaskinetic Bhatnagar-Gross-Krook (BGK) method, is developed and applied to the aerodynamic and aeroelastic computation of the ballute system for the flow range from continuum flow to transition flow regime. Followed the method developed by Dr. Xu [1], the BGK equation is solved with the finite-volume method, the flux at the cell interface is constructed with Van Leer's MUSCL method [2], and the non-equilibrium state is computed with the Chapman-Enskog expansion. The flux is derived by the moment of the gas distribution function. The steady solution is computed with the time marching method with either explicit or implicit algorithm. In order to compute the unsteady and aeroelastic cases, the dual-time method is implemented. Finally the BGK-NS3D solver is applied for the steady solution of modeled-ballute configuration. The steady solution is compared with experimental results. Furthermore, the BGK-NS3D solver is coupled with nonlinear computational structural solver DYNA3D, the static aeroelastic computational results are discussed. I. Introduction NE of NASA's new space programs is directed towards the unmanned Martian/Titan explorations. The entry vehicle design, to the surface of Mars or Titan and henceforth return with samples to earth, might be one which is flexible, deployable and inflatable decelerator of a ballute. The hypersonic entry of such vehicles will cover rarefied to continuum flow regimes, going through the transition flow regime of the Knudsen number range of [0<Kn<0.5]. Shown in Figure 1 are Earth/Mars entry profiles of the Knudsen number, Mach number, and dynamics pressure. It is seen that the peak dynamic pressure zone is critical for aeroelastic instability, and falls in the transition regime (0.0001<Kn<0.5) of the hypersonic entry. The flows of this rarefied hypersonic regime and the following supersonic to transonic regime are expected to interact strongly with the inflatable ballute during the course of its atmospheric entry. This type of interaction, called inflatable aeroelasticity, is highly nonlinear because of the expected large deformations of the inflatable structure and of the flow conditions during entry. In order to compute the aeroelastic performance of the ballute, a time-accurate Computational Fluid Dynamics (CFD) method is required. Compared with other methods for rarefied gas flow, e.g., DSMC (which has limitation for steady flow) and Lattice-Boltzmann equation (which is generally for low speed flow), the Kinetic BGK method of Xu, called BGK-NS method, [1,3~6] could be a potential candidate in that it is a time-accurate CFD method as it is unified in the transition to continuum flow regimes. Furthermore, the BGK-NS method compute the convective term and viscous term in one shot. And BGK-NS method has advantage in the compactness of the discretion stencil, offering a stable, mesh-independent discretization and a sound physical rooted in gas-kinetic theory. In this paper, the method developed for two-dimensional BGK solver is extended to the solution of threedimensional viscous on body-fitted grid. The second order accuracy cell-centered finite volume method is applied for to solve the BGK equation. The discretized equation will produce a Ordinary Differential Equation (ODE) equation. The ODE equation can be marched along time by Runge-Kutta integration or implicit scheme." @default.
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• W2313564936 date "2011-06-14" @default.
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• W2313564936 title "Development of a Three-Dimensional BGK Solver" @default.
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• W2313564936 doi "https://doi.org/10.2514/6.2011-3708" @default.
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