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联翼布局飞机具有优良的升阻特性,是下一代亚声速飞机优先选择的气动布局型式之一,但在某些情况下其俯仰力矩随迎角的增大会表现出较强的非线性变化特点.针对该问题,在Ma=0.75条件下,采用数值模拟方法对某亚声速联翼布局气动性能及其绕流流场进行研究,通过对各部件气动特性分析,结合不同前翼绕流流动状态下前/后翼绕流场特点及截面气动力分布特点,揭示了前翼对后翼绕流流场干扰是引起其俯仰力矩非线性变化的主要原因.计算结果表明:在一定迎角下,该联翼布局飞机前翼绕流发生分离,从而影响后翼绕流流场,引起后翼气动效率下降,导致全机俯仰力矩随飞机迎角发生非线性上扬,对该机飞行性能的提高带来严重影响.
The wing layout aircraft has excellent lift characteristics, is the next generation of the preferred choice of aerodynamic aircraft layout type, but in some cases its pitch moment increases with the angle of attack will show a strong non-linear change characteristics Aiming at the problem, under the condition of Ma = 0.75, the numerical simulation method is used to study the aerodynamic performance of a subsonic supersonic wing and the flow field around it. By analyzing the aerodynamic characteristics of each substructure, The characteristics of the front / rear wing around the flow field and the aerodynamic characteristics of the cross section show that the disturbance of the front wing to the flow field around the rear wing is the main reason causing the nonlinear variation of the pitch moment. The calculation results show that at a certain angle of attack, The wing layout of the front wing flow around the separation occurred, thus affecting the flow around the rear wing flow field, causing the aerodynamic efficiency of the rear wing decreased, resulting in the pitch angle of the aircraft with a non-linear rise in aircraft angle of attack on the aircraft flight performance improvement To seriously affect.