摘要
气动加热与结构热传递耦合问题在航天和工程应用领域非常重要。分别采用松耦合与紧耦合方法,数值模拟了高超声速二维圆管绕流的流场与结构传热耦合的非定常过程。在紧耦合方法中,流场部分采用基于Navier Stokes方程的有限体积法,将AUSM+格式与时间方向的显式多步Runge Kutta法结合;结构传热部分采用基于二维热传导方程的Galerkin有限元法。流场与结构区通过交界面的热流和温度边界条件实现耦合。计算结果分别与实验、文献做了对比,结构内部温度变化关系以及壁面的热流分布均较好地吻合。两种耦合方式的计算结果对比表明,对于流场特征时间远小于结构传热特征时间的问题,松耦合方法计算效率高,精度与紧耦合方法接近。
The coupling problems of aeroheating and solid heat penetration are very important to aerospace and engineering applications. The looselycoupled and the fullycoupled methodology are both applied to simulate a twodimensional hypersonic fluidsolid thermally coupled flow around a cylinder. The unsteady NavierStokes equations and the 2D unsteady heatconduction equation are derived, solved by the finite volume and the Galerkin finite element methods respectively. The coupling is processed by the boundary conditions of heat flux and temperature at the fluid/solid interface. The flow part is solved by AUSM+ and explicit multistep RungeKutta method. The results are compared with the experimental data and computational results from the reference. The method is shown to give good predictions of the temperature variation and heat flux distribution, and the looselycoupled method is shown to be more efficient and similar accurate if the characteristic time for fluid is far less than the time for solid.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2003年第1期35-39,共5页
Journal of National University of Defense Technology
