不同热边界对超音速机翼气动热数值分析的影响

飞行器在超音速飞行时受到的气动加热效应给结构强度及热防护设计带来极大影响，且真实状态下的气动热环境需要考虑外流场与结构的耦合及内壁面边界条件的影响。采用S-A湍流模型求解Navier-Stokes方程，通过流场与固体壁面交界处的信息传递，实现外流场与结构场的耦合数值分析。针对三种不同翼型的超音速绕流气动加热进行耦合数值研究，对比翼型内壁面在不同热边界条件下的气动热效应，结果表明：不同翼型具有与气动力相似的的气动热效应；内壁面考虑对流换热的边界条件最接近真实；考虑机翼燃油箱满油时，三维机翼前缘驻点处热流密度最高可达4200w/m2。

Influence of Different Thermal Boundary on Numerical Analysis of Aerodynamic Heat of Supersonic Wing

The aerodynamic heating effect of the aircraft during supersonic flight has a great impact on the structural strength and thermal protection design. The aerodynamic thermal environment in the real state needs to consider the coupling of the external flow field and the structure and the influence of the boundary conditions of the inner wall surface. The S-A turbulence model is used to solve the Navier-Stokes equation. The coupling of the flow field and the solid wall is used to realize the coupled numerical analysis of the external flow field and the structural field. The coupling numerical study of the supersonic flow aerodynamic heating of three different airfoils is carried out, and the aerodynamic thermal effects of the inner wall surface of the airfoil under different thermal boundary conditions are compared. The results show that different airfoils have aerodynamic thermal effects similar to aerodynamic forces. The boundary condition of the inner wall considering convective heat transfer is the closest to reality; considering the fuel tank of the wing is full, the heat flux at the leading edge of the 3D wing can be up to 4200w/m2.