双锥Bump压缩面设计及气动特性  

Bipyramid Bump compression surface design and aerodynamic characteristics

作　　者：王龙[1] 钟易成[1] 吴晴[2] 杨应凯[3] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国电子科技集团公司第三十八研究所,合肥230001 [3]中国航空工业集团公司成都飞机设计研究所,成都610015

出　　处：《航空动力学报》2013年第1期82-89,共8页Journal of Aerospace Power

基　　金：成都飞机设计所联合基金

摘　　要：采用反设计方法研究双锥Bump压缩面设计技术,该方法实质是融合运动间断边界在运动网格条件下对轴对称欧拉方程组求解.为避免激波捕获法对激波型面位置求解误差,应用计算域分块的方法预估第2道激波,在此基础上采用流线追踪法生成Bump压缩面;结合平面机身设计一双锥Bump实例,运用计算流体力学仿真手段对其进行黏性数值模拟.研究结果表明:①该模型流场结构仍保持较强的附面层扫掠能力;②在来流马赫数为2.0条件下,相比传统的正圆锥乘波体Bump压缩面设计,新型设计方法可使Bump外压缩系统总压恢复系数提高0.04左右,为Bump进气道性能提高奠定基础.An inverse design numerical method was introduced to investigate the design technique of new bipyramid bump compression surface.The axisymmetric Euler equations with the discontinuities boundary condition were solved on dynamic mesh using computational domain partition method which calculated the second shock wave in order to avoid solving the shock location error by shock capture method.On this basis,a bipyramid Bump example combined with the flat plane was designed by the streamline tracking method introduced to generate Bump compression surface,and it was simulated by computational fluid dynamics in viscosity.The results show that：（1） the model maintains a strong boundary layer swept capacity in the flow field structure;（2） at Mach number 2.0 condition,the method adopted here can make the total pressure recovery coefficient of the Bump compression system increases 0.04 compared to the traditional Bump compression surface based on cone waverider design,also lays the foundation for improving the Bump inlet performance.

关 键 词：Bump进气道 运动间断边界算法 反设计方法 运动间断拟合 计算流体力学 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]