三角翼无尾布局全动翼尖的操纵性能研究

 基于变前掠翼(VFSW)布局,采用Navier-Stokes控制方程的有限体积法离散格式,选取剪切应力输运(SST)湍流模型,对VFSW中三角翼飞行器全动翼尖(AMT)的流场进行数值分析。首先,通过未带机翼前缘延伸的三角翼试验模型验证了数值模拟算法的精度;其次,研究了三角翼无尾布局在超声速时AMT的操纵性能;最后,采用可视化方法分析了AMT的流场和作用机理。AMT计算结果表明:迎角对AMT偏航特性影响轻微,超声速时最大设计舵偏量的偏航力矩系数约为0.02,但偏航力矩和滚转力矩具有耦合性;耦合滚转力矩在局部大迎角时易反向,而舵面失升是滚转反向的根本原因;AMT的偏航作用线性较好,作动效率较高,消除不利滚转后是变前掠翼布局一种极具潜力的航向操纵面。

Study of Control Characteristics for All Moving Wing Tips in Delta Wing Tailless Configuration

An shear stress transport(SST) turbulence model is selected for a variable forward swept wing (VFSW) configuration, and the disperse format of the Navier-Stokes control equations with the finite volume method is employed to analyze numerically the flow fields of all moving wing tips (AMT) for a delta wing aircraft in VFSW configuration. First, the precision of the numerical simulative algorithm is validated by a comparison with the data of a delta wing experimental model without wing leading-edge extension. Second, the characteristics of the AMT for delta wing tailless configuration in a supersonic area are investigated. Finally, the flow fields and operative mechanism of the AMT are analyzed by streamline display. The computational results of the AMT show that the angle of attack has little effect on the characteristics of the AMT, and the yawing moment coefficient of the AMT with the designed maximum deflection angle in the supersonic area is about 0.02, but the yawing moment may be coupled with the rolling moment, and the coupled rolling moment will turn to the opposite direction at a large local angle, while the ultimate cause of the coupled opposite rolling moment is that the rudder loses lift. To sum up, for better linearity of yawing effect and greater yawing efficiency, the AMT is a potential yawing control surface for VFSW configuration provided its negative rolling moment is removed.