流向入射涡与后翼相互作用分析

涡翼互作用现象影响航空运输编队飞行的效益和配对进近的安全。采用数值模拟方法,针对无入射涡影响的后翼以及稳定状态下的入射涡位于后翼3个典型展向位置共4种情况,研究入射涡与后翼的相互作用。对比分析了基于Q准则的三维涡量、不同流向位置的涡量,以及后翼吸力面静压系数、气动参数和滚转力矩系数等。研究结果表明:稳定状态下的入射涡在后翼外侧时,翼尖涡受上洗运动影响;在内侧时,受下洗运动影响。两种情况下,翼尖涡强度均受到抑制。入射涡越靠近后翼翼尖,后翼升力系数、升阻比、滚转力矩系数越大,且在其与后翼翼尖重合时都达到最大值。这一结果可为编队飞行和配对进近的前后机布局提供参考。

Analysis of Interactions Between Streamwise-Oriented Vortex andFollower Wing

Vortex-wing interactions affect the efficiency of formation flights and the safety of paired approaches. A numerical simulation study is developed to investigate four situations, including a follower wing without stable incident vortex, and stable incident vortex on a follower wing at three typical spanwise locations. The vortex-wing interactions between stable incident vortex and a follower wing is studied. Three-dimension vorticity based on Q-criterion, vorticities at different streamwise locations, surface pressure coefficient in suction side, aerodynamic coefficients and rolling-moment coefficient are analyzed by comparison. The results show that, when the stable incident vortex is outside or inside the tip of the follower wing, the tip of the follower wing is at the down wash or up wash region. Wing-tip vortex is restrained in both locations. Lift coefficient, lift-to-drag ratio and rolling-moment coefficient increase as the stable incident vortex getting close to the tip of the follower wing and reach maximum, when incident vortex is coincide with the tip of the follower wing. Such results could provide references for formation flights and paired approaches.