高速飞行器逆向喷流全机减阻特性分析  

Characteristics of Whole-vehicle Drag Reduction in High-speed Vehicle Through Opposing Jet Flow

作　　者：杨天鹏 惠俊鹏 于江鹏 张立坤 YANG Tianpeng;HUI Junpeng;YU Jiangpeng;ZHANG Likun(Beijng Institute of Space Long Mach Vehicle,Beijing,100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术（中英文）》2024年第6期1-7,共7页Missiles and Space Vehicles

摘　　要：为了研究头部逆向喷流对全机阻力特性的影响,基于典型双锥飞行器计算模型,通过求解多组元轴对称Navier-Stokes方程,给出了头部逆向喷流来流高度参数和喷主流总压比参数对全机波阻、摩阻和底阻的影响规律。计算结果表明,喷主流总压比增加改变了流场结构使得波阻和底阻降低,并导致边界层内温度降低和速度梯度增加,在边界层速度梯度影响更大的条件下会出现摩阻增加的现象。在高空条件下,摩阻的占比较高且减阻效果较好,选择合适的总压比能有效降低总阻力;在低空条件下,底阻的占比较高且减阻效果较好,较大的总压比减阻效果更显著。高空低总压比的逆向喷流减阻与喷流流量消耗的效费比更优。To study the drag reduction characteristics of head opposing jet flow for the whole high-speed vehicle,a calculation model is established for sphere bicone,and flow field is solved by using multi-component axial symmetry Navier-Stokes equations.The influence laws of the opposing jet on the wave drag,friction drag,and base drag are studied by using the height of free stream,and the total pressure ratio of the jet and free stream.The calculation results show that the increase of the total pressure ratio reduces the wave drag and base drag by changing the flow field structure,and it leads to a temperature decrease and velocity gradient increase within the boundary layer.The dominant boundary velocity gradient can lead to an increase in friction drag.For high-altitude conditions,the friction drag has a high proportion of total drag and a better drag reduction effect,so it is better to choose an appropriate total pressure ratio.For low-altitude conditions,the base drag has a high proportion of total drag and a better drag reduction effect,so it is better to choose a high total pressure ratio.Considering the cost-effectiveness ratio of drag reduction and opposing jet mass flow,high-altitude flight conditions with a small total pressure ratio can be chosen.

关 键 词：数值模拟 逆向喷流 减阻 来流高度 喷主流总压比 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]