Abstract
:A new flow-thermal-structural coupling approach based on coupled heat transfer simulation is applied to the analysis of a hypersonic aerodynamically heated leading edge. The three-dimensional unsteady flow-thermal-structural coupling is studied for Mach Number 6.47 flow over a cylinder for which the flow behavior and aero-thermal loads are calibrated by experimental data, and the numerical results of surface pressure, cold-wall heating-rate, hot-wall heating-rate and temperature distributions are all well consistent with experimental data. Interactions between the flow, structural heat transfer and deformation as well as the requirement of grid resolution for k – ε – R turbulence model are also studied.
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