在高速风洞中对某武器舱舱门打开状态下，舱内的静压分布和脉动压力特性进行了试验，并对空腔前缘多孔扰流板和前缘吹气两种流动控制方法分别进行了变参数研究。试验马赫数为0.75，武器舱长度为300 mm，长深比为3，宽深比为1。试验结果表明该武器舱基本构型顶部沿着流向的压力分布比较均匀，脉动压力监测点的频谱特性表现出明显的模态特征，为开式空腔流动类型，而且在所研究的范围内受飞机迎角变化的影响很小。在典型的飞机迎角下，前缘多孔扰流板流动控制方法可以很好地改善武器舱内部流场的稳态特性并降低舱内的脉动压力；多孔扰流板的安装高度、展向宽度为流动控制效果的主要影响参数；在所研究的参数范围内，综合考虑多孔扰流板对脉动压力宽频和单频特性的控制效果，高安装高度、短展向宽度的参数组合形式最优，并且在飞机常用的迎角范围内具有较好的流动控制效果。在典型的飞机迎角下，前缘吹气流动控制方法也可以很好地改善武器舱内部流场的稳态特性并降低舱内的脉动压力；吹气位置、吹气流量为流动控制效果的主要影响参数；在所研究的参数范围内，综合考虑前缘吹气对脉动压力宽频和单频特性的控制效果，大的吹气流量、短的展向宽度的参数组合形式最优，并且在飞机常用的迎角范围内具有较好的流动控制效果。
The static and fluctuating pressure characteristics of cavity flow in a weapon bay were tested in a high speed wind tunnel, and the flow control method with perforated plate or injection which was added to the leading edge of the cavity was studied with changing parameters. The test Mach number 0.75, cavity length 300 mm, length-to-depth ratio 3, and width-to-depth ratio 1. Experimental results showed that on the ceiling of the cavity and along the flow direction, the pressure distribution is relatively uniform. The spectra for different monitor points showed the same modal characteristics, which is typical of open cavity flow and is barely affected by the change of angle of attack within a certain range. At the typical flight angle of attack, the flow control method of the leading-edge perforated plate can improve the pressure distribution along the flow direction and reduce the fluctuating pressure in the cavity. The installation height and the span-wise length of the perforated plate have a significant impact on the flow control effect. Within certain range, the combination of large installation height and small span-wise length has a better flow control effect on the perforated plate, which can also work steadily at different angles of attack. At the typical flight angle of attack, the flow control method of leading-edge injection can also improve the pressure distribution along the flow direction and reduce the fluctuating pressure in the cavity. The jet slot width and the jet flow rate have a significant impact on the flow control effect. Within certain range, the combination of small span-wise width and large jet flow rate has a better flow control effect on the leading-edge injection, which can also work steadily at different angles of attack.
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