翼梢侧向喷流干扰特性数值模拟

A numerical investigation of wing tip-mounted lateral jet interaction flowfield

当弹体表面安装喷管时,在喷管迎风条件下往往出现不利的侧向喷流干扰,翼梢安装喷管能减弱这种不利干扰.采用有限体积离散方法求解N-S方程,研究了旋成体-边条翼-舵组合体翼梢安装喷管的侧向喷流干扰特性和规律.分析了干扰流场结构和喷流干扰因子随Mach数、攻角、飞行高度等参数的变化特性.研究结果表明:翼梢喷流干扰形成了非常复杂的流场结构,虽然翼梢喷流远离弹体,仍对弹体、翼、舵上的载荷产生明显影响,在不同飞行条件下干扰范围和强度明显不同.喷流气动干扰因子规律复杂并呈非线性变化,干扰因子大于0.5的范围明显增加,有效增加了喷流控制使用范围.但在某些条件下仍然出现较大负值,产生严重不利干扰现象.

Disadvantageous lateral jet interaction often occurs in a windward orientation with missile body-mounted thrusters.The disadvantageous phenomenon can be decreased with the wing tip-mounted thrusters.The interaction flowfield induced by the wing tip-mounted lateral jets was presented by numerical simulation.The N-S equations were solved by finite volume methods.The flow characteristics and amplification factors with flow parameters,such as Mach number,angle of attack,flight height were analyzed.The results show that the surface and spatial structures of interaction flowfield are complex for the wing tip-mounted lateral jets interaction.Although the jets are far from projectile,but the loads on the missile body,wing and fins have a significant impact,and the interaction region and intensity are obviously different on different flight conditions.The rule of amplification factors is complex,and presents nonlinear changes,and the range in which lateral jet control is effective obviously increasing.But the amplification factors on certain conditions have a large negative value,and it presents serious disadvantageous interaction.