Prediction of flow field and thermal environment in the gap is crucial to the design of hypersonic vehicle thermal protection system. The compressible Navier-Stokes equation is solved to study the flow field and aerodynamic heating in the gap. The effect of inflow parameter on the aerodynamic heating is analyzed. The results show that there are vortex motions in the gap. The heat transfer in the gap mainly depends on the convection in the top region. The heat flux along the gap wall distributes in U-shape, and at the outlet of the gap is highest, which is the key point in the thermal protection design. As the angle of attack increases, the number of vortices will decrease gradually, and wall heat flux will increase, especially at the gap exit. The research results provide references for the design and optimization of thermal protection system.
The knowledge of the flow field inside the wind tunnel is an essential element for the identification of test experiment. For the sake of obtaining more insight of the flow propagation throughout a newly built wind tunnel, numerical simulation of the flow field is performed, and the Navier-Stokes equations are solved using the computational fluid dynamics (CFD) code Fluent. Experimental surveys of the wind tunnel flow with pressure sensors and thermocouple sensors are also performed, providing valuable data for the flow characterization. The Mach number, temperature and pressure in the core area of the wind tunnel are obtained, and the behavior of flow propagation is quantitatively described. The simulation results of the CFD model have a good agreement with the experimental data. Through this study, the flow field characteristics of the wind tunnel are obtained, which can provide some reference for future experiments.
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