Numerical Simulation of Fluid-solid-thermal Interaction in Hypersonic Flows
The fluid-solid-thermal interaction in hypersonic flows is simulated numerically by partitioned staggered procedures in this paper. The fluid and solid thermal fields are discretized in space by finite volume schemes and integrated in time by a staggered numerical scheme. The unsteady fully Navier-Stokes equations are solved for the flow field. Inviscid fluxes are dispersed by Harten-Yees TVD(Total Variation Diminishing) format and viscous fluxes are dispersed directly by central difference format. Dual time method is used to simulate the unsteady process. The 3D unsteady heat conduction equation is solved for the structure temperature field. The coupling is processed as follows: The flow field acquires temperatures boundary condition from the structure and the temperature field of the structure acquires heat fluxs boundary condition from flow at the fluid-solid interface. The method proposed here is applied for aerothermal nose of space shuttle successfully. The transformation of head of space shuttles temperature is detailedly analyzed during pneumatic heat. The results show that the increase of wall temperature strongly affects heat flux. Therefore, solid-fluid coupled iteration is very necessary in the simulation because the influence of the increase of wall temperature can be considered.
hypersonic pneumatic heat coupling structural heat transfer nose of space shuttle
Li Pengfei Wu Songping
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics,Beijing 100191,China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
428-431
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）