论文部分内容阅读
采用基于结构/非结构混合网格的CFD方法对栅格翼的亚跨声速气动特性进行了研究,计算方法经过试验数据的验证,可达到工程精度。对单独栅格翼的研究表明,跨声速壅塞时,流动通过栅格前方亚声速气流减速从栅格外侧溢流而实现流量调节;超声速壅塞时,流动通过在栅格翼上产生网状脱体激波使来流减速至亚声速来进行流量调节,且计算结果与理论估算上下临界马赫数范围一致。对某栅格翼气动布局导弹的计算结果表明,在跨声速壅塞区间内,壅塞有自我调节作用,通过溢流使栅格通道内维持相似流动,从而使栅格气动性能保持基本平稳;同时由于溢流使流量下降,栅格翼升力效率下降,导弹静稳定性减弱。
Adopting CFD method based on structured / unstructured mixed meshes to study the transonic aerodynamic characteristics of grid wings, the calculation method is verified by the experimental data to achieve engineering accuracy. Research on individual grid wings has shown that flow transits through the subsonic subsonic flow in front of the grid to achieve flow regulation when transonic clogs are throttled, and when supersonic choking, flows through the mesh wing The shock wave decelerates the flow to sub-sonic velocity to regulate the flow, and the calculated result is consistent with the theoretically estimated upper and lower critical Mach range. The calculated results of a grid-mounted wing layout missile show that the congestion has a self-regulating effect in the transonic congestion zone and maintains a similar flow in the grid channel by overflow, so that the aerodynamic performance of the grid remains stable. At the same time, The overflow reduces the flow rate, the lift efficiency of the grid wing decreases and the static stability of the missile weakens.