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为了研究攻角导致的来流定常/非定常变化对二元高超声速进气道性能的影响,在马赫3.85条件下,对一个设计马赫数为6.0的二元高超声速进气道进行了动态攻角变化的风洞实验。实验中,攻角在0°～8.2°连续变化,动态频率最大达到9.3Hz。实验研究表明:攻角在0°～8.2°连续变化过程中,进气道始终保持着起动状态;攻角增加使进气道出口增压比逐渐上升,流量系数、出口总压恢复系数和出口马赫数逐渐降低;在保持起动状态的攻角连续变化过程中,振荡的二元高超声速进气道其性能变化趋势与准稳态时相似,攻角的动态变化未对进气道性能产生显著影响。
In order to study the effect of steady / unsteady inflow on binary hypersonic inlet due to angle of attack, a binary hypersonic inlet with a Mach number of 6.0 was dynamited under Mach 3.85 Wind tunnel experiments with varying angles. In the experiment, the angle of attack changes continuously from 0 ° to 8.2 ° and the maximum dynamic frequency reaches 9.3 Hz. The experimental results show that the inlet is always in the starting state during the continuous 0 ° -8.2 ° angle of attack, and the increase of the angle of attack leads to the gradual increase of the pressure increasing ratio at the outlet of the air intake. The flow coefficient, the total outlet pressure recovery coefficient and the outlet The Mach number gradually decreases; during the continuous change of the attack angle with the starting state, the oscillation trend of binary hypersonic inlet is similar to that of the quasi-steady state, and the dynamic change of the angle of attack has no significant effect on the inlet performance influences.