摘要
采用流场解算器TRIP2.0(Trisonic Platform version 2.0),在与风洞测力试验比较的基础上,研究了多种跨超声速来流状态下某三角翼布局基本外形气动特性以及前缘涡的产生和发展。数值模拟结果揭示了在不同马赫数、攻角、侧滑角条件下,前缘涡的产生、发展和破裂过程及其对气动特性的影响。在背风区旋涡结构随马赫数的变化关系上,数值模拟结果显示,亚声速旋涡破裂发生在逆压区,破裂从涡轴上开始,超声速旋涡不易破裂,除非在激波的作用下变为亚声速旋涡,该结果在定性上与理论分析结果取得来了较好的一致。对有侧滑角状态下,背风区旋涡的流动特性进行了研究,得到一些有价值的结论。
The aerodynamic characteristics of delta wings is dominated by the leading edge vortex. Using flow solver TRIP2.0（Trisonic Platform version 2.0）, the generation and evolution of vortex structure from the leading edge of a delta wing for different transonic free stream conditions are studied, and the compari- sion with force measurent are presented also. Structure multiblock mesh, LUSGS solving method, high-or- der TVD scheme and SST turbulent models are selected to simulate the complicated flow field. Mutigrid technique is used to accelerate convergence speed. The generation, evolution and breakdown of the vortex and its influence on aerodynamic characteristics are analyzed for various parameters including Mach number, angle of attack and angle of sideslip . Numerical results show that the breakdown of subsonic vortex occurs in negative pressure region, and it starts from the vortex axis. It is not easy for a supersonic vortex to break- down, except that the vortex is changed to a subsonic one due to a shock wave. The vortex structure under typical angle of sideslip is studied carefully, some valuable conclusions are obtained.
出处
《空气动力学学报》
CSCD
北大核心
2013年第5期554-558,共5页
Acta Aerodynamica Sinica
基金
国家重点基础研究发展计划"数值风洞软件系统若干基础问题研究"(项目编号2009CB723800)
