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The flying vehicle will encounter severe aerodynamic heating and large drag due to shock wave when it is in hypersonic flight, spikes ahead of the blunt noses of bodies of revolution have been considered as a means of the total heat flux and aerodynamic drag reduction, while a conical shock wave induced by the spike instead of the former bow shock wave of the blunt body. In this paper, the influences...
The existence of viscosity effect at the interface of double dissimilar materials has an important impact to the distribution of interface crack-tip field and the properties variety of the interface itself. The singular is considered in crack-tip, and the elastic-viscoplastic quasi-static propagating governing equations of double dissimilar materials at interface crack-tip field are established. The...
The virtual displacement equation with visco-elasticity boundary condition is presented, the uniform mathematical expression of visco-elasticity boundary condition is reached. The FEPG(Finite Element Program Generator) system has the capacity of generating finite element computation program directly from virtual displacement equation the paper gets the finite element computation program according...
In order to discuss the material behavior of concrete subjected to fire, based on elastic-plastic theories, considering the variation of material properties with temperature, the general incremental thermo-elastic-plastic creep constitutive equation is derived in consideration of temperature and creep deformation. According to Drucker-Prager yield rules, the incremental thermo- elastic-plastic creep...
For the mechanical properties of reinforced concrete under high temperature with large deterioration, the reliability of reinforced concrete beams have been largely discounted. The plastic zone resistance of concrete under high temperature has been considered in this paper. A simple and feasible time-variant model of the resistance of reinforced concrete beams has been given under fire and a reliability...
The oscillations of the flow field around a hemispherical nose with a supersonic opposing jet in a free stream of Mach 3.98 are computed. Two total pressure ratios of a jet to a free stream 0.2 and 0.6 are examined, which correspond to unsteady flow and steady flow, respectively. The axisymmetric Navier-Stokes equations with Shear-Stress Transport (SST) turbulence model are used as the governing equations...
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