小展弦比飞翼布局飞机横向涡流控制气动机理

 为增加小展弦比飞翼布局飞机横向控制效能，设计了可提供飞机滚转力矩的涡流控制方案，在此基础上研究了三角翼前缘非对称垂直喷流对前缘涡破裂位置和结构的影响。应用三维任意坐标系下的雷诺平均N-S方程数值模拟方法和Spalart-Allmaras方程湍流模型，对小展弦比飞翼布局飞机前缘非对称喷流及无喷流情况下的绕流进行了研究分析。结果表明：与无喷流情况相比，喷流速度、喷口压力、飞行迎角的不同造成了涡破裂点的改变以及涡的强度和涡轴位置的变化，这些因素最终引起流场变化，并产生不对称力和力矩；喷流产生的直接力和力矩与飞行状态无太大关系；垂直喷流在进行横向控制同时产生较小的偏航力矩，对阻力的影响也较小。

Lateral Inject Active Vortex Control Based on Low Aspect Ratio Flying Wing

In order to improve the lateral control ability of the low aspect ratio flying wing aircraft, a vortex control method is designed which can provide rolling moment for the aircraft, and the effects of leading dissymmetrical vertical injects on flow structure are studied. High precision simulation of the Reynolds average N-S equations and the Spalart-Allmaras torrent model are used to study vortex flows over the low aspect ratio flying wing aircraft with and without leading dissymmetrical edge injects. The re...