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For the numerical simulation of the hypersonic vehicle aerothermal heating, the grid-dependency of the aerothermal computation under the hypersonic flow was studied by the means of computational fluid dynamic. By employed two-dimensional cylinder model, researched the influence of the grid-reynolds number Recell to heat transfer simulation, and established the connection between grid refinement in...
Turbulence and shock waves interactions occur in a wide range of applications, such as mixing, flow separation and combustion. However, it is still a challenge to accurately simulate these problems. The two demands seem contradictory: the simulation of small turbulence scales requires non-dissipative scheme while the capture of shock requires dissipative scheme. We evaluate the performance of several...
The study of high accuracy numerical schemes is a hot topic for decades in the field of compressible turbulence simulations. Linear compact schemes, high-order shock-capturing schemes and the hybrid schemes are three types of schemes used in today's turbulent flow simulations. The fifth-order compact scheme, WENO scheme and hybrid compact-WENO scheme are introduced as the representatives of these...
This paper proposes a method to make supersonic axisymmetric mixed-compression multi-inlets get into the single subcritical condition by numerical simulation. The flow mechanism in the inlets and the changing rule of the aerodynamic performance of the missile under this condition have been studied. The results when supersonic inlets get into single subcritical condition are concluded as follows: (1)...
Aimed at studying the influence of different defectors on impact properties of parallel LOX/kerosene engine exhaust plume, flow fields of double-nozzle and six-nozzle LOX/kerosene engine exhaust plume impacting on three diversion troughs of without deflector, with a wedge deflector, with a conical deflector were calculated with the CFD software, and influences of different deflectors on impact properties...
The paper suggests a modification of AUSMPW+ scheme designed to low Mach number. For Mach number vanishing, AUSMPW+ scheme has an excessive numerical dissipation to result in the incorrect scaling of pressure and density fluctuations. The modification rescales all velocity components in the numerical flux by the local Mach number. The improved method reduces the dissipation and recovers the correct...
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