论文部分内容阅读
构建了高超声速飞行器表面驻点及其下游区对流气动加热的一种快速预测方法.首先,采用工程方法计算飞行器表面无黏流场,针对工程方法的熵吞没效应,将质量流量平衡法与轴对称比拟法相结合对边界层外缘进行熵修正;其次,推导出采用线性方程拟合飞行器表面流场的拟合方程;在此基础上,发展出基于线性流场和线性物面方程的轴对称比拟法,大幅度降低了复杂度和计算量;对于驻点区域,引入隐式曲面拟合驻点主曲率半径并构造鲁棒的驻点区热流计算方法.采用球锥体和仿空天飞行器等多种外形验证了方法的有效性,计算结果表明:1)所述方法总耗时约1 s即可预测出气动加热,并且预测结果与CFD模拟或者试验测量数据比较一致;2)在飞行器表面流线扩展区域,进行熵修正可进一步提高预测精度,在流线不扩张区域,采用等熵或变熵无黏流场的预测结果差别微小.
A fast method of predicting the aerodynamic heating of the convective surface at the surface of a hypersonic vehicle and its downstream zone is established.Firstly, a viscous engulfing effect on the aircraft surface is calculated by engineering method, and the mass flow balance method is compared with the shaft The symmetry comparison method is used to modify the outer edge of the boundary layer. Secondly, the fitting equation of the flow field on the surface of the aircraft is derived by using the linear equation. On this basis, the axial symmetry based on linear flow field and linear object surface equation Compared with the method of comparison, the complexity and the amount of calculation are greatly reduced. For the stagnation point region, the implicit curved surface fitting principal curvature radius of the stagnation point is introduced and a robust method for calculating the heat flux in the stagnation point area is constructed. The results show that: 1) the method can predict aerodynamic heating with a total time of about 1 s, and the prediction results are consistent with the CFD simulation or experimental measurement data; 2) In the aircraft The surface streamline extension area, the entropy correction can further improve the prediction accuracy, in the streamline does not expand the area, the use of isentropic or entropy non-stick flow field prediction results are slightly different.