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基于轴对称比拟概念,发展了一套笛卡尔坐标系下的高超声速飞行器气动热环境计算方法。首先利用有限体积法数值求解Euler方程获得较为准确的边界层外缘无粘流场参数,然后基于有限元的四节点单元变换方法,直接利用笛卡尔坐标系下的三维速度分量计算无粘表面流线和尺度因子;在获取无粘表面流线和尺度因子的基础上,利用Zoby、Moss和Sutton提出的热流公式计算表面热流,从而实现数值算法和工程算法的耦合。将上述方法用于求解球锥在攻角分别为0°、8°和16°时的表面热流,并将计算结果同经典流线法结果及实验值进行比较,从而对方法进行考核验证。结果显示:本文计算结果与实验值吻合的较好,计算精度较经典流线法有较大提高。
Based on the concept of axial symmetry, a set of aerodynamic thermal environment calculation methods for hypersonic vehicles under Cartesian coordinates is developed. Firstly, the Euler equation was solved by using the finite volume method to get the more accurate viscous flow field boundary layer boundary parameters. Then based on the finite element method of four-node element transformation, the three-dimensional velocity component in Cartesian coordinate system was used to calculate the viscous flow Line and scale factor. On the basis of obtaining the non-stick surface flow line and scale factor, the surface heat flow is calculated by using the heat flow formula proposed by Zoby, Moss and Sutton, so as to realize the coupling of numerical algorithm and engineering algorithm. The above method is used to solve the surface heat flow when the angle of attack of the spherical cone is 0 °, 8 ° and 16 °, respectively. The calculated results are compared with the classical streamline method and the experimental data to verify the method. The results show that the calculated results are in good agreement with the experimental ones and the calculation precision is greatly improved compared with the classical streamline method.