超音速带弹武器舱气动特性数值研究

Numerical Research on Aerodynamic Characteristics of Cavity with Store at Supersonic Speeds

采用大涡模拟（LES）和计算声学FW-H方程相结合的方法,研究了带弹武器舱在超音速条件下的气动特性,建立了计算模型并验证了网格的可靠性。计算结果表明：带弹武器舱的流场由于导弹的分隔而形成3个独立旋涡,静压系数沿流向总体呈先减小后增大分布;流场噪声声压级比空腔流场低5~6 dB,最大声压级出现在弹舱后壁面两侧区域,声压级峰值频率小于200 Hz;流场噪声产生于舱口剪切层的自持振荡,在导弹头部和弹舱后壁面之间区域存在＂脱落涡—声波—反射声波—新脱落涡＂的循环。研究结果对建立适用于超音速带弹武器舱的流场控制方法有参考意义。

The aerodynamic characteristics of cavity with store at supersonic speeds are researched using large eddy simulation（LES） method and FW-H equations.A computational model is established,and the grid reliability is proved.The results show that the flow field is separated into three independent vortices because of the existence of missile,and the fluctuation of static pressure coefficient is enhanced.The sound pressure level（SPL） of cavity with store is 5 ~ 6 dB lower than that of empty cavity.The max SPLs are on both the sides of the cavity aft-wall,and the peak frequency is below 200 Hz.Flow field sound is generated from the self-sustained oscillation of shear layer.The sound generation cycle is＂shed vorticessound wave-reflection sound wave-new shed vortices＂,which exists in the area between the head of missile and the aft-wall of cavity.These results can be used to build the control method for flow field of cavity with store at supersonic speeds.