弹用S弯进气道气动性能试验

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 pneumatic characteristics for S-shaped inlet in missiles

Abstract: Experimental investigation of an S-shaped inlet has been done 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 and 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 of high incidence and yaw, the total pressure recovery is low and the distortion is high, but the performance will be better if the yaw angle increases farther.(4)At the matching point of the inlet and engine ,the power spectrum of the flow at the exit is like white noise and not sensitive to the variation of attitude angle and free stream Mach number.(5)When the engine is running under small mass flow ,the inlet model surge occurs, the frequency of surge is 150Hz.