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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。
Based on the VFSW layout and the finite volume method discrete method of the Navier-Stokes control equation, the shear stress transport (SST) turbulence model was selected to simulate the flow of the full wing tip (AMT) Field for numerical analysis. First of all, the accuracy of the numerical simulation algorithm is verified by the experimental model of the delta wing without the extension of the leading edge of the wing. Secondly, the maneuverability of the delta-wing tailless arrangement at supersonic velocity is studied. Finally, the visualization method is used to analyze the flow of the AMT Field and mechanism of action. The results of AMT show that the angle of attack has a slight influence on the yawing characteristics of AMT. The yaw moment coefficient of the maximum design rudder deflection at supersonic speed is about 0.02, but the yawing moment and the rolling moment are coupled. It is easy to reverse the angle of attack and the rudder is the root cause of roll reversal. The yawing effect of AMT is better and its operating efficiency is higher. Potential course control surface.