高超声速流动与换热数值仿真研究

A finite-difference unsteady coupled heat transfer solver was developed. This solver was utilized to simulate the hypersonic flow over a backward-facing step with a transverse gap, and the unsteady thermal conduction in an infinite circular pipe. The backward-facing step leads to local dramatically changing distributions of aerodynamic parameters and wall heat fluxes. The gas flow in the gap decelerates rapidly along with the increase of the gap depth, and there is rather weak convective heat transfer at the bottom of the gap. In the case of hypersonic flow around the infinitely long circular pipe, there exists large temperature gradient in the boundary layer, and the wall temperature increases with time, otherwise the aerodynamic parameters outside the boundary layer change quite slightly. The predicted results are in good agreement with the tested data. The comparison between numerical simulation results and tested data verifies the calculation ability of the developed solver.