摘要
综合考虑理想乘波体的优缺点,设计了一种类乘波构型高超声速飞行器机体并针对其布局特点进行了钝化。按照等总压恢复系数原则设计二维前体,二维后体下表面和侧缘分别采用三次曲线和"上反"形式,得到了具有较好气动性能的类乘波构型机身。根据这种类乘波构型边缘线的特点,分别对前缘和侧缘进行了钝化。前缘采用了增加材料的钝化方法,钝化曲线为圆弧曲线;针对侧缘提出了一种基于三次Bézier曲线的钝化方法,这种钝化方法同时对侧面的上边缘和下边缘进行了处理,不仅保证了侧面连续光滑,而且增大了机身的容积。采用数值模拟方法研究了该钝化方法对这种类乘波构型气动力和气动热性能的影响。数值计算结果表明,钝化对气动力影响较小,对气动热影响较大,边缘钝化使升阻比降低了13%,但最大热流密度减少了77%。研究结果表明,这种钝化方法较好平衡了类乘波构型高超声速飞行器的气动力和气动热性能,可以为高超声速飞行器的外形设计提供参考。
Considering the advantages and disadvantages of ideal waverider comprehensively, a kind of quasi-waverider hypersonic vehicle body was designed and the bluntness was carried out according to its configuration characteristics. 2D forebody was designed according to the principle of constant total pressure recovery coefficient. Cubic curve and ‘side edge upward’ was used to the design of after body and side edge, respectively. The quasi-waverider vehicle body with good performance was obtained. According to the characteristics of the quasi-waverider, the leading edge and the sharp side edge were blunted, respectively. A method of increasing material was used to blunt the leading edge, of which the blunt curve is a circular curve. A blunt method based on cubic Bézier curve was proposed for the sharp side edges. At the basis, the sharp side edges of top and bottom were blunted simultaneously, which not only ensure a continuous smooth side surface, but also increase volume of the quasi-waverider. The effect of the blunt method on the aerodynamic force and aerodynamic heating of this configuration was studied by numerical simulation. Numerical calculation results show that aerodynamic force is less dependent on the bluntness, whereas the aerodynamic heating is greater influenced. The lift-drag ratio is reduced by 13% due to blunt leading edge, while the maximum heat flux decreases by 77%. Investigation shows that the aerodynamic force and aerodynamic heating performance of quasi-waverider hypersonic aircraft are well balanced by this blunt method, which can be used for the configuration design of hypersonic vehicle.
作者
罗浩
张艳华
张登成
郑无计
LUO Hao;ZHANG Yanhua;ZHANG Dengcheng;ZHENG Wuji(Institute of Aeronautics Engineering,Air Force Engineering University,Xi'an 710038,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第3期383-392,共10页
Journal of Solid Rocket Technology
关键词
类乘波构型
钝化
数值模拟
升阻比
热流密度
quasi-waverider
bluntness
numerical simulation
lift-drag ratio
heat flux
