论文部分内容阅读
通过有限体积法和二阶迎风格式,对弧形翼-身组合体流场进行了数值仿真研究。研究结果给出了弧形翼气动特性随飞行马赫数[Ma=1.5～5.5]的变化,其静态稳定性的损失变化和滚转力矩系数的变化规律,且详细分析了弧形翼在零攻角下产生自诱导滚转力矩的原因。数值计算结果与国外的风洞实验结果进行比较,发现与JPL飞行实验有较好的吻合性。
The finite element method and the second-order upwind method are used to simulate the flow field of arc-wing-body combination. The results show that the aerodynamic characteristics of the arc wing vary with the flight Mach number [Ma = 1.5-5.5], the variation of the static stability and the variation of the rolling torque coefficient, The reason for the self-induced roll moment is generated under the angle. The numerical results are compared with the results of wind tunnel experiments in other countries and found to be in good agreement with the JPL flight test.