Abstract
Taking a wing of the hypersonic aircraft as the research object, a fluid-thermal-solid coupling analysis of a two-dimensional flow around circular pipe model was simulated in MpCCI platform, which combining Fluent and Abaqus. The result was verified by the typical hypersonic flow around two-dimensional round tube unsteady experiment. It shows that the position of the shock wave and the density distribution of the flow field can be accurately calculated based on the k - ω SST turbulence model in the simulation of flow field outside the tube. The stagnation temperature of the tube is 378.7 K when T was 2s, and the relative error is 2.6% compared with the experiment. On that basis, the temperature and the stress distributions of the wing is simulated under the 2 seconds aerodynamic heating time at different Mach numbers. The results show that the wall temperature and Mises increased gradually with the increasing velocity, but the rising trend of temperature and Mises decreased gradually, and the maximum temperature appears near the leading edge of the wing, Mises decreased gradually along chord and span directions. The maximum deformation appears at the trailing edge of the wing and the elastic deformation of the whole structure is positively correlated with the temperature, and the deformed area is located at the wing tip.
Published Version
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