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中文核心期刊

充气结构与流场的耦合求解方法

Model of inflatable structure/fluid interaction for variable leading edge

  • 摘要: 针对一种充气前缘(inflatable leading edge, ILE)增升技术,建立了其充气结构与流场耦合作用的运动方程. 将方程写成状态空间形式,采用时域推进方法求解. 对使用了变前缘增升技术的NACA63-212翼型进行了充气结构静变形的数值计算,结果表明充气结构的刚度对翼型的气动特性有明显影响. 与原翼型相比,在不考虑充气结构变形时, 该增升技术大约能使翼型的失速迎角增加30\%,最大升力系数增加22\%;考虑结构变形后增升效果有所降低. 刚度较低的薄膜在前缘吸力峰的作用下会隆起形成鼓包,容易引起流动分离.

     

    Abstract: The paper presents the interactive motion equation ofinflatable structure in flow. The inflatable structure is used in thetechnique of a variable leading edge for high lift. The interaction betweenstructure and fluid is a typically aeroelastic problem. The motion equation isobtained through the analytic solution of an infinitesimal element in thediscrete membrane. Coupled with Navier--Stokes equation, the aeroelasticequation was solved with time-marching methods, and the aerodynamiccharacteristics of NACA 63-212 airfoil with the inflatable leading edge(ILE) were obtained. From the results, the ILE technique has been applied tosignificantly increase the stall angle of attack and lift coefficient.The values of stall angle of attack and maximum lift coefficient wereenhanced to be 30 percent and 22 percent, respectively. In addition, thedeformation of ILE greatly influenced the flow around the airfoil while theelastic coefficient of material was low. The inflatable structure near thesuck peak deformed clearly, and this hump could induce the separation inadvance.

     

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