摘要
采用鸭翼展向吹气间接涡控技术,对后掠角为50°的主翼和鸭翼气动布局进行数值模拟,给出不同吹气动量系数下的数值模拟结果,建立了鸭翼吹气动量系数与布局气动力系数之间的关系。并针对该布局模型,将风洞测力、测压以及水洞流动显示试验结果与数值模拟结果进行了详细的分析比较,结果表明,对鸭翼实施展向吹气技术,确实可以延迟和控制主翼涡破裂、增大升力的效果,在大迎角下把鸭翼作为涡发生器对主翼进行控制是可行的,计算结果与试验结果定性上是吻合的,是可以模拟这种复杂流场的。
Associating with advantages of the close-coupled canard-wing configuration and wing-spanwise blowing,the indirect-vortex-control technology of canard-spanwise blowing has been used,Using the canard as a vortex generator,the canard-spanwise blowing can strengthen the canard vortex,by making use of the advantageous interaction between canard and wing vortex,the strength of wing vortex is enhanced,the lift is increased,and the high-attack and post-stall maneuverability of fi ghter are improved.In this paper,the model which the sweep angle of main wing is 50° and the sweep angle of canard is 50°,has been built in FLUENT and numerical simulated in different jet momentum coeff icients at a certain angle,then get the result of the relationship between jet momentum coeff icients and the aerodynamic forces;analyze the results of the simulation at the aspect of lift coefficient,pressure coeffi cient,flow condition contrasting to the force and pressure measurement in wind tunnel and flow visualization in water tunnel,and then show the discipline of the enhancing wing vortex,delaying wing vortex breakdown,increasing the lift coefficient,guiding the design of new generation of fighters.
出处
《飞机设计》
2010年第5期7-11,30,共6页
Aircraft Design
基金
国防预研基金项目(9140A13020307HK0127
9140A13040109HK149)资助
关键词
鸭翼布局
间接涡控制技术
展向吹气
数值模拟
canard configuration
indirect-vortex-control technology
spanwise blowing
numerical simulation
