高超声速升力体气动力气动热数值计算

Aerodynamic and aerothermal numerical simulation of hypersonic lifting body configuration

升力体气动布局 ,由于其良好的高超声速气动特性、有效的内部空间和有益的防热特性 ,越来越受到气动工作者的重视 ,本文应用张涵信院士的NND格式思想 ,用数值模拟的方法对类似于美国X 33的升力体外形进行了气动力、气动热研究。特别是在粘性项的离散和表面热流率的计算中应用了散度和梯度的积分定义 ,避免了数值计算的奇异性 ,保证了通量守恒 ,提高了计算效率。结果表明气动热计算结果与美国同类飞行器结果接近 ,驻点热流率与经典理论结果一致。

The researchers are paying more attention to lifting body aerodynamic configuration because of its favorable aerodynamic character, effective inner space and beneficial thermal protection character. This paper uses Zhang Hanxin's NND scheme to study the aerodynamic and aerothermal character of a lifting body like X 33 of America. Specially we utitize the integral definition of gradient and divergence when dispersing the viscosity term and calculating the surface thermal flow rate, so we may avoid the simulation singularity, assure the flux conservation and increase the calculation efficiency. It shows that the aerothermal result approaches the result of similar vehicle of America and the thermal flow rate at the stagnation point is consistent with the classical result.