弹用S弯进气道气动性能试验  

Experimental investigation of pneumatic characteristics for S-shaped inlet in missiles

作　　者：靖建朋[1,2] 郭荣伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国人民解放军驻西飞集团军事代表室,西安710089

出　　处：《航空动力学报》2009年第9期2085-2090,共6页Journal of Aerospace Power

摘　　要：对一种弹用S弯进气道进行了试验,结果表明:①偏航角一定,攻角由负到正变化时,总压恢复系数先上升后变化不大,|DC60|则先下降后小幅升高;②攻角一定,总压恢复系数和|DC60|随偏航角的增加均呈先升高后降低的趋势;③大的攻角和偏航角组合状态下,总压恢复系数较低,|DC60|偏大,但随偏航角进一步增大,进气道性能有所改善;④进/发匹配点处,进气道出口压力功率频谱较平坦且对姿态角和来流马赫数的变化均不敏感;⑤发动机小流量状态时,进气道模型发生了喘振,频率约为150 Hz.Experimental investigation of an S-shaped inlet was made in this paper.The results show that: 1) When the yaw angle is constant and the attack angle changes from negative to positive,the total pressure recovery increases at first and then keeps almost constant,while the distortion coefficient drops at first and then rises a little.2) When the attack angle is constant and the yaw angle increases,the total pressure recovery and distortion coefficient increase at first and then decline.3) Under the combination...

关 键 词：S弯进气道 攻角 偏航角 总压恢复系数 畸变指数 功率频谱 进气道喘振 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]