控制面偏转方式对前掠翼静气弹特性的影响

Numerical Study on Influence of Control Surfaces on Aero-elastic Characteristics of Forward-swept Wing

针对不同控制面偏转方式对弹性前掠翼静气弹特性的影响,基于计算流体力学/计算结构力学(CFD/CSD)松耦合静气动弹性数值计算方法,计算和分析了不同迎角、动压及马赫数条件下前、后缘控制面联合偏转对前掠翼模型的气动特性和弹性变形特性的影响。计算结果表明:控制面偏转对前掠翼飞机静气动弹性特性影响较大;当迎角变化,同向偏转方式的气动特性和弹性变形特性较好,α=4°时,弹性机翼的升阻特性较好;当动压变化时,反向偏转方式的气动特性和弹性特性占优,最大升阻比较同向偏转提高约7%,反向偏转方式气动特性较好,最大升阻比较同向偏转提高约7%;当马赫数变化时,弹性机翼条件下3种模型分别在Ma=0.7时升力系数达到最大值。计算结果可以为前掠翼飞机的实际应用提供参考。

A numerical simulation based on computational fluid dynamics/computational structural dynamics(CFD/CSD)loose coupling static aero elastic numerical calculation method is presented for elastic forward-swept wing(FSW)with control surfaces for its aero-elastic characteristics.The calculation and analysis on aero-elastic characteristics of the elastic FSW with control surfaces are performed under conditions of different angle of attack,dynamic pressure and mach numbers.The calculation result shows that the control surface deflection has great influence on FSW static aero-elastic characteristics;the aerodynamic and elastic deformation characteristics of elastic FSW rank first when leading-and trailing-edge control surfaces deflect in same direction with different angles of attack,and the lift-drag characteristics of elastic FSW is fairly good when α=4°.The aerodynamic and elastic deformation characteristics of elastic FSW are quite good when leading-and trailing-edge control surfaces deflect in different direction with different dynamic pressure,and the maximum lift-drag ratio is ahead of about 7%;The lift coefficient of all elastic models is the best when Ma=0.7.The study provides reference for real use of FSW only.